WorldWideScience

Sample records for low-speed high-turbulence flows

  1. Particle deposition in low-speed, high-turbulence flows

    DEFF Research Database (Denmark)

    Reck, Mads; Larsen, Poul Scheel; Ullum, U.

    2002-01-01

    field measurements. Particle deposition is shown to be associated with near-wall coherent structures. Flow reversal, simulated by impulsive start, is shown to give higher deposition rates than steady mean flows. Key word index: Spoilage fungi; spores; food processing plant; deposition flux; large eddy......, active and passive samplers provide typical values of airborne concentrations and specific deposition fluxes. Velocity and turbulence data from field studies are used as input in LES simulations of the process, and estimates of deposition fluxes are of the same order of magnitude as those deduced from...... simulation....

  2. Evaporation of polydispersed droplets in a highly turbulent channel flow

    Science.gov (United States)

    Cochet, M.; Bazile, Rudy; Ferret, B.; Cazin, S.

    2009-09-01

    A model experiment for the study of evaporating turbulent two-phase flows is presented here. The study focuses on a situation where pre-atomized and dispersed droplets vaporize and mix in a heated turbulent flow. The test bench consists in a channel flow with characteristics of homogeneous and isotropic turbulence where fluctuations levels reach very high values (25% in the established zone). An ultrasonic atomizer allows the injection of a mist of small droplets of acetone in the carrier flow. The large range diameters ensure that every kind of droplet behavior with regards to turbulence is possible. Instantaneous concentration fields of the vaporized phase are extracted from fluorescent images (PLIF) of the two phase flow. The evolution of the mixing of the acetone vapor is analyzed for two different liquid mass loadings. Despite the high turbulence levels, concentration fluctuations remain significant, indicating that air and acetone vapor are not fully mixed far from the injector.

  3. Evaporation of polydispersed droplets in a highly turbulent channel flow

    Energy Technology Data Exchange (ETDEWEB)

    Cochet, M.; Bazile, Rudy; Ferret, B.; Cazin, S. [INPT, UPS, IMFT (Institut de Mecanique des Fluides de Toulouse), Universite de Toulouse (France)

    2009-09-15

    A model experiment for the study of evaporating turbulent two-phase flows is presented here. The study focuses on a situation where pre-atomized and dispersed droplets vaporize and mix in a heated turbulent flow. The test bench consists in a channel flow with characteristics of homogeneous and isotropic turbulence where fluctuations levels reach very high values (25% in the established zone). An ultrasonic atomizer allows the injection of a mist of small droplets of acetone in the carrier flow. The large range diameters ensure that every kind of droplet behavior with regards to turbulence is possible. Instantaneous concentration fields of the vaporized phase are extracted from fluorescent images (PLIF) of the two phase flow. The evolution of the mixing of the acetone vapor is analyzed for two different liquid mass loadings. Despite the high turbulence levels, concentration fluctuations remain significant, indicating that air and acetone vapor are not fully mixed far from the injector. (orig.)

  4. Logarithmic boundary layers in highly turbulent Taylor-Couette flow

    CERN Document Server

    Huisman, Sander G; Cierpka, Christian; Kahler, Christian J; Lohse, Detlef; Sun, Chao

    2013-01-01

    We provide direct measurements of the boundary layer properties in highly turbulent Taylor-Couette flow up to $\\text{Ta}=6.2 \\times 10^{12}$ using high-resolution particle image velocimetry (PIV). We find that the mean azimuthal velocity profile at the inner and outer cylinder can be fitted by the von K\\'arm\\'an log law $u^+ = \\frac 1\\kappa \\ln y^+ +B$. The von K\\'arm\\'an constant $\\kappa$ is found to depend on the driving strength $\\text{Ta}$ and for large $\\text{Ta}$ asymptotically approaches $\\kappa \\approx 0.40$. The variance profiles of the local azimuthal velocity have a universal peak around $y^+ \\approx 12$ and collapse when rescaled with the driving velocity (and not with the friction velocity), displaying a log-dependence of $y^+$ as also found for channel and pipe flows [1,2].

  5. Measurements of the tip-gap turbulent flow structure in a low-speed compressor cascade

    Science.gov (United States)

    Tang, Genglin

    This dissertation presents results from a thorough study of the tip-gap turbulent flow structure in a low-speed linear compressor cascade wind tunnel at Virginia Tech that includes a moving belt system to simulate the relative motion between the tip and the casing. The endwall pressure measurements and the surface oil flow visualizations were made on a stationary endwall to obtain the flow features and to determine the measurement profiles of interest. A custom-made miniature 3-orthogonal-velocity-component fiber-optic laser-Doppler velocimetry (LDV) system was used to measure all three components of velocity within a 50 mum spherical measurement volume within the gap between the endwall and the blade tip, mainly for the stationary wall with 1.65% and 3.30% tip gaps as well as some initial experiments for the moving wall. Since all of the vorticity in a flow originates from the surfaces under the action of strong pressure gradient, it was very important to measure the nearest-wall flow on the endwall and around the blade tip. The surface skin friction velocity was measured by using viscous sublayer velocity profiles, which verified the presence of an intense lateral shear layer that was observed from surface oil flow visualizations. All second- and third-order turbulence quantities were measured to provide detailed data for any parallel CFD efforts. The most complete data sets were acquired for 1.65% and 3.30% tip gap/chord ratios in a low-speed linear compressor cascade. This study found that tip gap flows are complex pressure-driven, unsteady three-dimensional turbulent flows. The crossflow velocity normal to the blade chord is nearly uniform in the and tip-gap and changes substantially from the pressure to suction side. The crossflow velocity relies on the local tip pressure loading that is different from the mid-span pressure loading because of tip leakage vortex influence. The tip gap flow is highly skewed three-dimensional flow throughout the full gap

  6. Rigid spherical particles in highly turbulent Taylor-Couette flow

    Science.gov (United States)

    Bakhuis, Dennis; Verschoof, Ruben A.; Mathai, Varghese; Huisman, Sander G.; Lohse, Detlef; Sun, Chao

    2016-11-01

    Many industrial and maritime processes are subject to enormous frictional losses. Reducing these losses even slightly will already lead to large financial and environmental benefits. The understanding of the underlying physical mechanism of frictional drag reduction is still limited, for example, in bubbly drag reduction there is an ongoing debate whether deformability and bubble size are the key parameters. In this experimental study we report high precision torque measurements using rigid non-deformable spherical particles in highly turbulent Taylor-Couette flow with Reynolds numbers up to 2 ×106 . The particles are made of polystyrene with an average density of 1.036 g cm-3 and three different diameters: 8mm, 4mm, and 1.5mm. Particle volume fractions of up to 6% were used. By varying the particle diameter, density ratio of the particles and the working fluid, and volume fraction of the particles, the effect on the torque is compared to the single phase case. These systematic measurements show that adding rigid spherical particles only results in very minor drag reduction. This work is financially supported by Netherlands Organisation for Scientific Research (NWO) by VIDI Grant Number 13477.

  7. Accurate measurement of streamwise vortices in low speed aerodynamic flows

    Science.gov (United States)

    Waldman, Rye M.; Kudo, Jun; Breuer, Kenneth S.

    2010-11-01

    Low Reynolds number experiments with flapping animals (such as bats and small birds) are of current interest in understanding biological flight mechanics, and due to their application to Micro Air Vehicles (MAVs) which operate in a similar parameter space. Previous PIV wake measurements have described the structures left by bats and birds, and provided insight to the time history of their aerodynamic force generation; however, these studies have faced difficulty drawing quantitative conclusions due to significant experimental challenges associated with the highly three-dimensional and unsteady nature of the flows, and the low wake velocities associated with lifting bodies that only weigh a few grams. This requires the high-speed resolution of small flow features in a large field of view using limited laser energy and finite camera resolution. Cross-stream measurements are further complicated by the high out-of-plane flow which requires thick laser sheets and short interframe times. To quantify and address these challenges we present data from a model study on the wake behind a fixed wing at conditions comparable to those found in biological flight. We present a detailed analysis of the PIV wake measurements, discuss the criteria necessary for accurate measurements, and present a new dual-plane PIV configuration to resolve these issues.

  8. Effect of passive flow-control devices on turbulent low-speed base flow

    Science.gov (United States)

    Heidari-Miandoab, Farid

    Some configurations of blunt trailing-edge airfoils are known to have a lower pressure drag compared to sharp trailing-edge airfoils. However, this advantage in addition to the structural advantage of a thick trailing-edge airfoil is offset by its high base drag. At subsonic velocities, this is attributed to the low-pressure base flow dominated by a Karman vortex street. In the limiting case, the steady separated flow over a rearward-facing step is attained if the periodically shed vortices from a blunt trailing-edge are suppressed by the addition of a base spiltter-plate. Experimental studies in the Old Dominion University Low-Speed Closed-Circuit Wind Tunnel were conducted to examine the effect of several passive flow-control devices such as Wheeler doublets and wishbone vortex generators, longitudinal surface grooves, base cavities, and serrations on the characteristics of two- and three-dimensional base flows. Flow over flat-plate airfoil and rearward-facing step models was studied in the turbulent incompressible subsonic flow regime. Models with trailing-edge and step-sweep angles of 0, 30, and 45 degrees with respect to the crossflow direction were considered. Constant-temperature hot-wire anemometry, infrared surface thermography, and pitot-static probes were used to conduct flow measurements. The parameters measured included vortex shedding frequency, convective heat-transfer rates, base pressure, and flow reattachment distance. Surveys of mean velocity profiles in the wake were also conducted. Results have shown that most of the flow control devices tested increased the base pressure of the 2-D and 3-D flat-plate airfoils. Use of longitudinal surface grooves resulted in shorter flow reattachment distances and higher convective heat transfer rates downstream of the 2-D rearward-facing steps.

  9. High-resolution methods for incompressible and low-speed flows

    CERN Document Server

    Drikakis, Dimitris

    2006-01-01

    This book covers the basic techniques for simulating incompressible and low-speed flows with high fidelity in conjunction with high-resolution methods. This includes techniques for steady and unsteady flows with high-order time integration and multigrid methods, as well as specific issues associated with interfacial and turbulent flows. The book is addressed to a broad readership, including engineers and scientists concerned with the development or application of computational methods for fluid flow problems in: Mechanical, Aerospace, Civil and Chemical Engineering, Biological Flows, Atmospheric and Oceanographic Applications as well as other Environmental disciplines. It can be used for teaching postgraduate courses on Computational Fluid Dynamics and Numerical Methods in Engineering and Applied Mathematics, and can also be used as a complementary textbook in undergraduate CFD courses.

  10. Multiple states in highly turbulent Taylor-Couette flow

    CERN Document Server

    Huisman, Sander G; Sun, Chao; Lohse, Detlef

    2016-01-01

    The ubiquity of turbulent flows in nature and technology makes it of utmost importance to fundamentally understand turbulence. Kolmogorov's 1941 paradigm suggests that for strongly turbulent flows with many degrees of freedom and its large fluctuations, there would only be \\emph{one} turbulent state as the large fluctuations would explore the entire higher-dimensional phase space. Here we report the first conclusive evidence of multiple turbulent states for large Reynolds number $\\text{Re}=\\mathcal{O}(10^6)$ (Taylor number $\\text{Ta}=\\mathcal{O}(10^{12})$) Taylor-Couette flow in the regime of ultimate turbulence, by probing the phase space spanned by the rotation rates of the inner and outer cylinder. The manifestation of multiple turbulent states is exemplified by providing combined global torque and local velocity measurements. This result verifies the notion that bifurcations can occur in high-dimensional flows i.e. very large $\\text{Re}$) and questions Kolmogorov's paradigm.

  11. Loss reduction in axial-flow compressors through low-speed model testing

    Science.gov (United States)

    Wisler, D. C.

    1984-01-01

    A systematic procedure for reducing losses in axial-flow compressors is presented. In this procedure, a large, low-speed, aerodynamic model of a high-speed core compressor is designed and fabricated based on aerodynamic similarity principles. This model is then tested at low speed where high-loss regions associated with three-dimensional endwall boundary layers flow separation, leakage, and secondary flows can be located, detailed measurements made, and loss mechanisms determined with much greater accuracy and much lower cost and risk than is possible in small, high-speed compressors. Design modifications are made by using custom-tailored airfoils and vector diagrams, airfoil endbends, and modified wall geometries in the high-loss regions. The design improvements resulting in reduced loss or increased stall margin are then scaled to high speed. This paper describes the procedure and presents experimental results to show that in some cases endwall loss has been reduced by as much as 10 percent, flow separation has been reduced or eliminated, and stall margin has been substantially improved by using these techniques.

  12. Loss reduction in axial-flow compressors through low-speed model testing

    Science.gov (United States)

    Wisler, D. C.

    1984-01-01

    A systematic procedure for reducing losses in axial-flow compressors is presented. In this procedure, a large, low-speed, aerodynamic model of a high-speed core compressor is designed and fabricated based on aerodynamic similarity principles. This model is then tested at low speed where high-loss regions associated with three-dimensional endwall boundary layers flow separation, leakage, and secondary flows can be located, detailed measurements made, and loss mechanisms determined with much greater accuracy and much lower cost and risk than is possible in small, high-speed compressors. Design modifications are made by using custom-tailored airfoils and vector diagrams, airfoil endbends, and modified wall geometries in the high-loss regions. The design improvements resulting in reduced loss or increased stall margin are then scaled to high speed. This paper describes the procedure and presents experimental results to show that in some cases endwall loss has been reduced by as much as 10 percent, flow separation has been reduced or eliminated, and stall margin has been substantially improved by using these techniques.

  13. Universal intermittent properties of particle trajectories in highly turbulent flows

    DEFF Research Database (Denmark)

    Arnèodo, A.; Benzi, R.; Berg, Jacob

    2008-01-01

    We present a collection of eight data sets from state-of-the-art experiments and numerical simulations on turbulent velocity statistics along particle trajectories obtained in different flows with Reynolds numbers in the range R-lambda is an element of [120740]. Lagrangian structure functions fro...

  14. Heat transfer effects on the stability of low speed plane Couette-Poiseuille flow

    Energy Technology Data Exchange (ETDEWEB)

    Oezgen, Serkan [Middle East Technical University, Department of Aerospace Engineering, Ankara (Turkey); Dursunkaya, Zafer [Middle East Technical University, Department of Mechanical Engineering, Ankara (Turkey); Ebrinc, Ali A. [FORD Otosan, Kocaeli (Turkey)

    2007-10-15

    The stability problem of low-speed plane Couette-Poiseuille flow of air under heat transfer effects is solved numerically using the linear stability theory. Stability equations obtained from two-dimensional equations of motion and their boundary conditions result in an eigenvalue problem that is solved using an efficient shoot-search technique. Variable fluid properties are accounted for both in the basic flow and the perturbation (stability) equations. A parametric study is performed in order to assess the roles of moving wall velocity and heat transfer. It is found that the moving wall velocity and the location of the critical layers play decisive roles in the instability mechanism. The flow becomes unconditionally stable whenever the moving wall velocity exceeds half of the maximum velocity in the channel. With wall heating and Mach number effects included, the flow is stabilized. (orig.)

  15. Discrete unified gas kinetic scheme for all Knudsen number flows: low-speed isothermal case.

    Science.gov (United States)

    Guo, Zhaoli; Xu, Kun; Wang, Ruijie

    2013-09-01

    Based on the Boltzmann-BGK (Bhatnagar-Gross-Krook) equation, in this paper a discrete unified gas kinetic scheme (DUGKS) is developed for low-speed isothermal flows. The DUGKS is a finite-volume scheme with the discretization of particle velocity space. After the introduction of two auxiliary distribution functions with the inclusion of collision effect, the DUGKS becomes a fully explicit scheme for the update of distribution function. Furthermore, the scheme is an asymptotic preserving method, where the time step is only determined by the Courant-Friedricks-Lewy condition in the continuum limit. Numerical results demonstrate that accurate solutions in both continuum and rarefied flow regimes can be obtained from the current DUGKS. The comparison between the DUGKS and the well-defined lattice Boltzmann equation method (D2Q9) is presented as well.

  16. Evaporation of bi-component droplets in a heated, highly turbulent flow

    Energy Technology Data Exchange (ETDEWEB)

    Moreau, F.; Bazile, R. [Universite de Toulouse, INPT, UPS, IMFT, Institut de Mecanique des Fluides de Toulouse, Toulouse (France); CNRS, IMFT, Toulouse (France)

    2012-08-15

    This work aims to understand the phenomena that occur in a combustion chamber where multi-component fuel droplets are injected. Many evaporation models exist but the influence of turbulence on spray vaporization is not yet well understood. This study gives a useful database to improve these models. The objective of the work is to measure the dispersion and the evaporation of bi-component (octane/3-pentanone) droplets and the resulting vapor mixing in a well-known, heated, highly turbulent channel flow. The carrier flow shows high turbulence levels, flat profiles for the mean velocity and the velocity fluctuations. The injected droplets have a large variety of behaviors due to the large polydispersion and to the turbulence. The evolution of 3-pentanone liquid concentration, mass flux, and droplet clusters are described. Mean concentration, fluctuations of concentration, and mixing of the vapor phase are characterized. (orig.)

  17. Chebyshev collocation spectral lattice Boltzmann method for simulation of low-speed flows.

    Science.gov (United States)

    Hejranfar, Kazem; Hajihassanpour, Mahya

    2015-01-01

    In this study, the Chebyshev collocation spectral lattice Boltzmann method (CCSLBM) is developed and assessed for the computation of low-speed flows. Both steady and unsteady flows are considered here. The discrete Boltzmann equation with the Bhatnagar-Gross-Krook approximation based on the pressure distribution function is considered and the space discretization is performed by the Chebyshev collocation spectral method to achieve a highly accurate flow solver. To provide accurate unsteady solutions, the time integration of the temporal term in the lattice Boltzmann equation is made by the fourth-order Runge-Kutta scheme. To achieve numerical stability and accuracy, physical boundary conditions based on the spectral solution of the governing equations implemented on the boundaries are used. An iterative procedure is applied to provide consistent initial conditions for the distribution function and the pressure field for the simulation of unsteady flows. The main advantage of using the CCSLBM over other high-order accurate lattice Boltzmann method (LBM)-based flow solvers is the decay of the error at exponential rather than at polynomial rates. Note also that the CCSLBM applied does not need any numerical dissipation or filtering for the solution to be stable, leading to highly accurate solutions. Three two-dimensional (2D) test cases are simulated herein that are a regularized cavity, the Taylor vortex problem, and doubly periodic shear layers. The results obtained for these test cases are thoroughly compared with the analytical and available numerical results and show excellent agreement. The computational efficiency of the proposed solution methodology based on the CCSLBM is also examined by comparison with those of the standard streaming-collision (classical) LBM and two finite-difference LBM solvers. The study indicates that the CCSLBM provides more accurate and efficient solutions than these LBM solvers in terms of CPU and memory usage and an exponential

  18. Numerical Simulation of Combustion and Extinction of a Solid Cylinder in Low-Speed Cross Flow

    Science.gov (United States)

    Tien, J. S.; Yang, Chin Tien

    1998-01-01

    The combustion and extinction behavior of a diffusion flame around a solid fuel cylinder (PMMA) in low-speed forced flow in zero gravity was studied numerically using a quasi-steady gas phase model. This model includes two-dimensional continuity, full Navier Stokes' momentum, energy, and species equations with a one-step overall chemical reaction and second-order finite-rate Arrhenius kinetics. Surface radiation and Arrhenius pyrolysis kinetics are included on the solid fuel surface description and a parameter Phi, representing the percentage of gas-phase conductive heat flux going into the solid, is introduced into the interfacial energy balance boundary condition to complete the description for the quasi-steady gas-phase system. The model was solved numerically using a body-fitted coordinate transformation and the SIMPLE algorithm. The effects of varying freestream velocity and Phi were studied. These parameters have a significant effect on the flame structure and extinction limits. Two flame modes were identified: envelope flame and wake flame. Two kinds of flammability limits were found: quenching at low-flow speeds due to radiative loss and blow-off at high flow speeds due to insufficient gas residence time. A flammability map was constructed showing the existence of maximum Phi above which the solid is not flammable at any freestream velocity.

  19. Analysis of Low Speed Stall Aerodynamics of a Swept Wing with Laminar Flow Glove

    Science.gov (United States)

    Bui, Trong T.

    2014-01-01

    Reynolds-Averaged Navier-Stokes (RANS) computational fluid dynamics (CFD) analysis was conducted to study the low-speed stall aerodynamics of a GIII aircraft's swept wing modified with a laminar-flow wing glove. The stall aerodynamics of the gloved wing were analyzed and compared with the unmodified wing for the flight speed of 120 knots and altitude of 2300 ft above mean sea level (MSL). The Star-CCM+ polyhedral unstructured CFD code was first validated for wing stall predictions using the wing-body geometry from the First American Institute of Aeronautics and Astronautics (AIAA) CFD High-Lift Prediction Workshop. It was found that the Star-CCM+ CFD code can produce results that are within the scattering of other CFD codes considered at the workshop. In particular, the Star-CCM+ CFD code was able to predict wing stall for the AIAA wing-body geometry to within 1 degree of angle of attack as compared to benchmark wind-tunnel test data. Current results show that the addition of the laminar-flow wing glove causes the gloved wing to stall much earlier than the unmodified wing. Furthermore, the gloved wing has a different stall characteristic than the clean wing, with no sharp lift drop-off at stall for the gloved wing.

  20. Analysis of Low-Speed Stall Aerodynamics of a Swept Wing with Laminar-Flow Glove

    Science.gov (United States)

    Bui, Trong T.

    2014-01-01

    Reynolds-Averaged Navier-Stokes (RANS) computational fluid dynamics (CFD) analysis was conducted to study the low-speed stall aerodynamics of a GIII aircraft's swept wing modified with a laminar-flow wing glove. The stall aerodynamics of the gloved wing were analyzed and compared with the unmodified wing for the flight speed of 120 knots and altitude of 2300 ft above mean sea level (MSL). The Star-CCM+ polyhedral unstructured CFD code was first validated for wing stall predictions using the wing-body geometry from the First American Institute of Aeronautics and Astronautics (AIAA) CFD High-Lift Prediction Workshop. It was found that the Star-CCM+ CFD code can produce results that are within the scattering of other CFD codes considered at the workshop. In particular, the Star-CCM+ CFD code was able to predict wing stall for the AIAA wing-body geometry to within 1 degree of angle of attack as compared to benchmark wind-tunnel test data. Current results show that the addition of the laminar-flow wing glove causes the gloved wing to stall much earlier than the unmodified wing. Furthermore, the gloved wing has a different stall characteristic than the clean wing, with no sharp lift drop-off at stall for the gloved wing.

  1. Vortex/Body Interaction and Sound Generation in Low-Speed Flow

    Science.gov (United States)

    Kao, Hsiao C.

    1998-01-01

    The problem of sound generation by vortices interacting with an arbitrary body in a low-speed flow has been investigated by the method of matched asymptotic expansions. For the purpose of this report, it is convenient to divide the problem into three parts. In the first part the mechanism of the vortex/body interaction, which is essentially the inner solution in the inner region, is examined. The trajectories for a system of vortices rotating about their centroid are found to undergo enormous changes after interaction; from this, some interesting properties emerged. In the second part, the problem is formulated, the outer solution is found, matching is implemented, and solutions for acoustic pressure are obtained. In the third part, Fourier integrals are evaluated and predicated results presented. An examination of these results reveals the following: (a) the background noise can be either augmented or attenuated by a body after interaction, (b) sound generated by vortex/body interaction obeys a scaling factor, (C) sound intensity can be reduced substantially by positioning the vortex system in the "favorable" side of the body instead of the "unfavorable" side, and (d) acoustic radiation from vortex/bluff-body interaction is less than that from vortex/airfoil interaction under most circumstances.

  2. Exploring the phase space of multiple states in highly turbulent Taylor-Couette flow

    CERN Document Server

    van der Veen, Roeland C A; Dung, On-Yu; Tang, Ho L; Sun, Chao; Lohse, Detlef

    2016-01-01

    We investigate the existence of multiple turbulent states in highly turbulent Taylor-Couette flow in the range of $\\mathrm{Ta}=10^{11}$ to $9\\cdot10^{12}$, by measuring the global torques and the local velocities while probing the phase space spanned by the rotation rates of the inner and outer cylinder. The multiple states are found to be very robust and are expected to persist beyond $\\mathrm{Ta}=10^{13}$. The rotation ratio is the parameter that most strongly controls the transitions between the flow states; the transitional values only weakly depend on the Taylor number. However, complex paths in the phase space are necessary to unlock the full region of multiple states. Lastly, by mapping the flow structures for various rotation ratios in a Taylor-Couette setup with an equal radius ratio but a larger aspect ratio than before, multiple states were again observed. Here, they are characterized by even richer roll structure phenomena, including, for the first time observed in highly turbulent TC flow, an ant...

  3. Exploring the phase space of multiple states in highly turbulent Taylor-Couette flow

    Science.gov (United States)

    van der Veen, Roeland C. A.; Huisman, Sander G.; Dung, On-Yu; Tang, Ho L.; Sun, Chao; Lohse, Detlef

    2016-06-01

    We investigate the existence of multiple turbulent states in highly turbulent Taylor-Couette flow in the range of Ta =1011 to 9 ×1012 by measuring the global torques and the local velocities while probing the phase space spanned by the rotation rates of the inner and outer cylinders. The multiple states are found to be very robust and are expected to persist beyond Ta =1013 . The rotation ratio is the parameter that most strongly controls the transitions between the flow states; the transitional values only weakly depend on the Taylor number. However, complex paths in the phase space are necessary to unlock the full region of multiple states. By mapping the flow structures for various rotation ratios in a Taylor-Couette setup with an equal radius ratio but a larger aspect ratio than before, multiple states are again observed. Here they are characterized by even richer roll structure phenomena, including an antisymmetrical roll state.

  4. Steady and Unsteady Casingwall Flow Phenomena in a Single-Stage Low-Speed Compressor at Part-Load Conditions

    Directory of Open Access Journals (Sweden)

    H. Saathoff

    2003-01-01

    Full Text Available This article describes an investigation of the casingwall flow phenomena in a single-stage, axial-flow, low-speed compressor at part-load conditions, utilizing an oil-flow technique to visualize the boundary layer development and highfrequency sensors to measure ensemble-averaged velocity and flow-angle distributions as well as unsteady total pressure distributions. Representative results are shown and discussed. The results enable different sources of endwall blockage to be identified and changes with flow rate to be determined.

  5. Concurrent Flame Growth, Spread and Extinction over Composite Fabric Samples in Low Speed Purely Forced Flow in Microgravity

    Science.gov (United States)

    Zhao, Xiaoyang; T'ien, James S.; Ferkul, Paul V.; Olson, Sandra L.

    2015-01-01

    As a part of the NASA BASS and BASS-II experimental projects aboard the International Space Station, flame growth, spread and extinction over a composite cotton-fiberglass fabric blend (referred to as the SIBAL fabric) were studied in low-speed concurrent forced flows. The tests were conducted in a small flow duct within the Microgravity Science Glovebox. The fuel samples measured 1.2 and 2.2 cm wide and 10 cm long. Ambient oxygen was varied from 21% down to 16% and flow speed from 40 cm/s down to 1 cm/s. A small flame resulted at low flow, enabling us to observe the entire history of flame development including ignition, flame growth, steady spread (in some cases) and decay at the end of the sample. In addition, by decreasing flow velocity during some of the tests, low-speed flame quenching extinction limits were found as a function of oxygen percentage. The quenching speeds were found to be between 1 and 5 cm/s with higher speed in lower oxygen atmosphere. The shape of the quenching boundary supports the prediction by earlier theoretical models. These long duration microgravity experiments provide a rare opportunity for solid fuel combustion since microgravity time in ground-based facilities is generally not sufficient. This is the first time that a low-speed quenching boundary in concurrent spread is determined in a clean and unambiguous manner.

  6. Fast PSP measurements of wall-pressure fluctuation in low-speed flows: improvements using proper orthogonal decomposition

    Science.gov (United States)

    Peng, Di; Wang, Shaofei; Liu, Yingzheng

    2016-04-01

    Fast pressure-sensitive paint (PSP) is very useful in flow diagnostics due to its fast response and high spatial resolution, but its applications in low-speed flows are usually challenging due to limitations of paint's pressure sensitivity and the capability of high-speed imagers. The poor signal-to-noise ratio in low-speed cases makes it very difficult to extract useful information from the PSP data. In this study, unsteady PSP measurements were made on a flat plate behind a cylinder in a low-speed wind tunnel (flow speed from 10 to 17 m/s). Pressure fluctuations (Δ P) on the plate caused by vortex-plate interaction were recorded continuously by fast PSP (using a high-speed camera) and a microphone array. Power spectrum of pressure fluctuations and phase-averaged Δ P obtained from PSP and microphone were compared, showing good agreement in general. Proper orthogonal decomposition (POD) was used to reduce noise in PSP data and extract the dominant pressure features. The PSP results reconstructed from selected POD modes were then compared to the pressure data obtained simultaneously with microphone sensors. Based on the comparison of both instantaneous Δ P and root-mean-square of Δ P, it was confirmed that POD analysis could effectively remove noise while preserving the instantaneous pressure information with good fidelity, especially for flows with strong periodicity. This technique extends the application range of fast PSP and can be a powerful tool for fundamental fluid mechanics research at low speed.

  7. Calculations of the flow resistance and heat emission of a sphere in the laminar and high-turbulent gas flows

    Science.gov (United States)

    Simakov, N. N.

    2016-12-01

    An early drag crisis can occur at high turbulence of incoming gas flow to a sphere. To study the influence of a crisis on heat transfer from a sphere to gas, a numerical experiment was carried out in which the free gas flow around a sphere with a temperature lower than the sphere temperature was simulated for two cases. The flow was laminar in the first case and highly turbulent in the second case. To take into account turbulence, the kinematic coefficient of turbulent viscosity with a value, which is much higher (up to 2000 times) than that for physical viscosity, was introduced. The results of calculations show that the early drag crisis occurs at Reynolds numbers of about 100 and results in considerable (by four to seven times) decrease in the hydrodynamic force and sphere drag coefficient C d . The early drag crisis is also accompanied by the crisis of heat transfer from a sphere to gas with a decrease in Nusselt numbers Nu by three to six times.

  8. NASA low-speed centrifugal compressor for 3-D viscous code assessment and fundamental flow physics research

    Science.gov (United States)

    Hathaway, M. D.; Wood, J. R.; Wasserbauer, C. A.

    1991-01-01

    A low speed centrifugal compressor facility recently built by the NASA Lewis Research Center is described. The purpose of this facility is to obtain detailed flow field measurements for computational fluid dynamic code assessment and flow physics modeling in support of Army and NASA efforts to advance small gas turbine engine technology. The facility is heavily instrumented with pressure and temperature probes, both in the stationary and rotating frames of reference, and has provisions for flow visualization and laser velocimetry. The facility will accommodate rotational speeds to 2400 rpm and is rated at pressures to 1.25 atm. The initial compressor stage being tested is geometrically and dynamically representative of modern high-performance centrifugal compressor stages with the exception of Mach number levels. Preliminary experimental investigations of inlet and exit flow uniformly and measurement repeatability are presented. These results demonstrate the high quality of the data which may be expected from this facility. The significance of synergism between computational fluid dynamic analysis and experimentation throughout the development of the low speed centrifugal compressor facility is demonstrated.

  9. Development of the Seeding System Used for Laser Velocimeter Surveys of the NASA Low-Speed Centrifugal Compressor Flow Field

    Science.gov (United States)

    Wasserbauer, C. A.; Hathaway, M. D.

    1994-01-01

    Consideration is given to an atomizer-based system for distributing high-volume rates of polystyrene latex (PSL) seed material developed to support laser velocimeter investigations of the NASA Low-Speed Compressor flow field. Complete evaporation of the liquid carrier before the flow entering the compressor was of primary concern for the seeder system design. It is argued that the seed nozzle should incorporate a needle valve that can mechanically dislodge accumulated PSL seed material when the nozzle is turned off. Water is less expensive as the liquid carrier and should be used whenever adequate residence times are available to ensure complete evaporation. PSL agglomerates over time and needs to be mixed or blended before use. Arrangement of the spray nozzles needs to be adjustable to provide maximum seeding at the laser probe volume.

  10. Laser Anemometer Measurements of the Three-Dimensional Rotor Flow Field in the NASA Low-Speed Centrifugal Compressor

    Science.gov (United States)

    Hathaway, Michael D.; Chriss, Randall M.; Strazisar, Anthony J.; Wood, Jerry R.

    1995-01-01

    A laser anemometer system was used to provide detailed surveys of the three-dimensional velocity field within the NASA low-speed centrifugal impeller operating with a vaneless diffuser. Both laser anemometer and aerodynamic performance data were acquired at the design flow rate and at a lower flow rate. Floor path coordinates, detailed blade geometry, and pneumatic probe survey results are presented in tabular form. The laser anemometer data are presented in the form of pitchwise distributions of axial, radial, and relative tangential velocity on blade-to-blade stream surfaces at 5-percent-of-span increments, starting at 95-percent-of-span from the hub. The laser anemometer data are also presented as contour and wire-frame plots of throughflow velocity and vector plots of secondary velocities at all measurement stations through the impeller.

  11. Enhancement of Oscillatory Flap Propulsors for Low Speed Flows in Water

    Science.gov (United States)

    2010-07-13

    in efficiency results from a reduction in the induced drag created by the lifting surface. Many of these modifications such as winglets , tip bulbs...one of the many terms that account for the total power loss. Thus, winglet -type tip modifications for the OFD are expected to lead to an...experiencing turbulent flow. Since the rear wing experiences turbulent flow due to upstream conditions, the rough composite skin might not be necessary to

  12. Supercritical droplet dynamics and emission in low speed cross-flows

    Energy Technology Data Exchange (ETDEWEB)

    Chae, J. W. [Korea Aerospace Research Institute, Daejeon (Korea, Republic of); Yang, H. S.; Yoon, W. S. [Yonsei University, Seoul (Korea, Republic of)

    2008-08-15

    Droplet dynamics and emission of a supercritical droplet in crossing gas stream are numerically investigated. Effects of ambient pressure and velocity of nitrogen gas on the dynamics of the supercritical oxygen droplet are parametrically examined. Unsteady conservative axisymmetric Navier-Stokes equations in curvilinear coordinates are preconditioned and solved by dual-time stepping method. A unified property evaluation scheme based on a fundamental equation of state and extended corresponding-state principle is established to deal with thermodynamic non-idealities and transport anomalies. At lower pressures and velocities of nitrogen cross flows, both the diffusion and the convection are important in determining the droplet dynamics. Relative flow motion causes a secondary breakup and cascading vortices, and the droplet lifetime is reduced with increasing in ambient pressure. At higher ambient pressures and velocities, however, the droplet dynamics become convection-controlled while the secondary breakup is hindered by reduced diffusivity of the oxygen. Gas-phase mixing depends on the convection and diffusion velocities in conjunction with corresponding droplet deformation and flow interaction. Supercritical droplet dynamics and emission is not similar with respect to the pressure and velocity of the ambient gas and thus provides no scale

  13. Coupling Analysis of Low-Speed Multiphase Flow and High-Frequency Electromagnetic Field in a Complex Pipeline Structure

    Directory of Open Access Journals (Sweden)

    Xiaokai Huo

    2014-01-01

    Full Text Available Accurate estimation of water content in an oil-water mixture is a key technology in oil exploration and production. Based on the principles of the microwave transmission line (MTL, the logging probe is an important water content measuring apparatus. However, the effects of mixed fluid flow on the measurement of electromagnetic field parameters are rarely considered. This study presents the coupling model for low-speed multiphase flow and high-frequency electromagnetic field in a complex pipeline structure. We derived the S-parameter equations for the stratified oil/water flow model. The corresponding relationship between the S-parameters and water holdup is established. Evident coupling effects of the fluid flow and the electromagnetic field are confirmed by comparing the calculated S-parameters for both stratified and homogeneous flow patterns. In addition, a multiple-solution problem is analyzed for the inversion of dielectric constant from the S-parameters. The most sensitive phase angle range is determined to improve the detection of variation in the dielectric constant. Suggestions are proposed based on the influence of the oil/water layer on measurement sensitivity to optimize the geometric parameters of a device structure. The method proposed elucidates how accuracy and sensitivity can be improved in water holdup measurements under high water content conditions.

  14. Natural laminar flow airfoil design considerations for winglets on low-speed airplanes

    Science.gov (United States)

    Vandam, C. P.

    1984-01-01

    Winglet airfoil section characteristics which significantly influence cruise performance and handling qualities of an airplane are discussed. A good winglet design requires an airfoil section with a low cruise drag coefficient, a high maximum lift coefficient, and a gradual and steady movement of the boundary layer transition location with angle of attack. The first design requirement provides a low crossover lift coefficient of airplane drag polars with winglets off and on. The other requirements prevent nonlinear changes in airplane lateral/directional stability and control characteristics. These requirements are considered in the design of a natural laminar flow airfoil section for winglet applications and chord Reynolds number of 1 to 4 million.

  15. Analysis of tonal noise generating mechanisms in low-speed axial-flow fans

    Science.gov (United States)

    Canepa, Edward; Cattanei, Andrea; Zecchin, Fabio Mazzocut

    2016-08-01

    The present paper reports a comparison of experimental SPL spectral data related to the tonal noise generated by axial-flow fans. A nine blade rotor has been operated at free discharge conditions and in four geometrical configurations in which different kinds of tonal noise generating mechanisms are present: large-scale inlet turbulent structures, tip-gap flow, turbulent wakes, and rotor-stator interaction. The measurements have been taken in a hemi-anechoic chamber at constant rotational speed and, in order to vary the acoustic source strength, during low angular acceleration, linear speed ramps. In order to avoid erroneous quantitative evaluations if the acoustic propagation effects are not considered, the acoustic response functions of the different test configurations have been computed by means of the spectral decomposition method. Then, the properties of the tonal noise generating mechanisms have been studied. To this aim, the constant-Strouhal number SPL, obtained by means of measurements taken during the speed ramps, have been compared with the propagation function. Finally, the analysis of the phase of the acoustic pressure has allowed to distinguish between random and deterministic tonal noise generating mechanisms and to collect information about the presence of important propagation effects.

  16. Algorithmic localisation of noise sources in the tip region of a low-speed axial flow fan

    Science.gov (United States)

    Tóth, Bence; Vad, János

    2017-04-01

    An objective and algorithmised methodology is proposed to analyse beamform data obtained for axial fans. Its application is demonstrated in a case study regarding the tip region of a low-speed cooling fan. First, beamforming is carried out in a co-rotating frame of reference. Then, a distribution of source strength is extracted along the circumference of the rotor at the blade tip radius in each analysed third-octave band. The circumferential distributions are expanded into Fourier series, which allows for filtering out the effects of perturbations, on the basis of an objective criterion. The remaining Fourier components are then considered as base sources to determine the blade-passage-periodic flow mechanisms responsible for the broadband noise. Based on their frequency and angular location, the base sources are grouped together. This is done using the fuzzy c-means clustering method to allow the overlap of the source mechanisms. The number of clusters is determined in a validity analysis. Finally, the obtained clusters are assigned to source mechanisms based on the literature. Thus, turbulent boundary layer - trailing edge interaction noise, tip leakage flow noise, and double leakage flow noise are identified.

  17. The Role of Tip Leakage Flow in Triggering Rotating Stall of a Low Speed Compressor under Inlet Distortion

    Institute of Scientific and Technical Information of China (English)

    Jingxuan Zhang; Feng Lin; Jingyi Chen; Chaoqun Nie

    2009-01-01

    The stall behavior in a single-stage low-speed axial compressor under rotating inlet distortion (RID) is investi-gated in the first half of this paper. The tests demonstrate that the tip leakage flow (TLF) plays an important rolein triggering rotating stall. The tracking of the spike-like disturbances caused by the spillage of TLV indicates that most of such spike-like disturbances will be smeared by non-distorted sector and the growth of the spike-like dis-turbances actually relate closely to how and how often the path of the propagating disturbances come across the path of the rotating distorted sector. In the second half of this paper, micro air injections are applied to test the ef-fect behavior of TLF on stall inception. Contrasts to without micro air injections, the spike-like disturbances are much fewer, so the possibilities that spike-like disturbances may trigger rotating stall are fewer too. As a result, the compressor gets a lower mass flow rate at stall for both co-rotating inlet distortion and counter-rotating inlet distortion.

  18. Identification and control of large-scale structures in highly turbulent shear flow

    Science.gov (United States)

    Schadow, K. C.; Wilson, K. J.; Gutmark, E.

    Unforced and forced subsonic jets were studied using hot-wire anemometry. It is found that highly coherent flow structure can be generated in the initial region of ducted flow by applying forcing to the flow innstability frequencies. Flow visualization experiments in water showed that the coherent structures had relatively high azimuthal coherence and were periodic in time and space. The convection velocity of the structures was about 60 percent of the mean flow velocity. Mixing of the shear layer with the surrounding recirculation zone and the inside core was enhanced by the forcing and reduced their size accordingly. Photographs from the flow visualization tests are provided.

  19. Applicability of linearized-theory attached-flow methods to design and analysis of flap systems at low speeds for thin swept wings with sharp leading edges

    Science.gov (United States)

    Carlson, Harry W.; Darden, Christine M.

    1987-01-01

    Low-speed experimental force and data on a series of thin swept wings with sharp leading edges and leading and trailing-edge flaps are compared with predictions made using a linearized-theory method which includes estimates of vortex forces. These comparisons were made to assess the effectiveness of linearized-theory methods for use in the design and analysis of flap systems in subsonic flow. Results demonstrate that linearized-theory, attached-flow methods (with approximate representation of vortex forces) can form the basis of a rational system for flap design and analysis. Even attached-flow methods that do not take vortex forces into account can be used for the selection of optimized flap-system geometry, but design-point performance levels tend to be underestimated unless vortex forces are included. Illustrative examples of the use of these methods in the design of efficient low-speed flap systems are included.

  20. Calibration of a γ-Reθ transition model and its validation in low-speed flows with high-order numerical method

    Directory of Open Access Journals (Sweden)

    Wang Yuntao

    2015-06-01

    Full Text Available Based on the Reynolds-averaged Navier–Stokes (RANS equations and structured grid technology, the calibration and validation of γ-Reθ transition model is preformed with fifth-order weighted compact nonlinear scheme (WCNS, and the purpose of the present work is to improve the numerical accuracy for aerodynamic characteristics simulation of low-speed flow with transition model on the basis of high-order numerical method study. Firstly, the empirical correlation functions involved in the γ-Reθ transition model are modified and calibrated with experimental data of turbulent flat plates. Then, the grid convergence is studied on NLR-7301 two-element airfoil with the modified empirical correlation. At last, the modified empirical correlation is validated with NLR-7301 two-element airfoil and high-lift trapezoidal wing from transition location, velocity profile in boundary layer, surface pressure coefficient and aerodynamic characteristics. The numerical results illustrate that the numerical accuracy of transition length and skin friction behind transition location are improved with modified empirical correlation function, and obviously increases the numerical accuracy of aerodynamic characteristics prediction for typical transport configurations in low-speed range.

  1. Subharmonic tonal noise from backflow vortices radiated by a low-speed ring fan in uniform inlet flow.

    Science.gov (United States)

    Magne, Stéphan; Moreau, Stéphane; Berry, Alain

    2015-01-01

    In order to highlight the mechanisms responsible for subharmonic tonal noise, a complete aeroacoustic study of a ring fan in presence of a uniform inlet flow is conducted. Unsteady RANS simulations with a compressible flow solver are used to compute the flow field and identify the acoustic sources on the rotor. The tip clearance recirculation shows upstream vortices that impinge the rotor blades and create the main source of unsteadiness on the fan. Since these vortices rotate at a lower speed than the rotor, the frequency of the impact is lower than the blade passing frequency. The acoustic signature is computed by propagating the noise sources located on the rotor surfaces using two methods: A Ffowcs-Williams and Hawkings analogy in the time-domain and an analytical model in the frequency-domain based on the compact rotating dipole formulation. A comparison with experimental results confirms that the aeroacoustic phenomena responsible for the subharmonic tonal noise are well captured and properly propagated by the acoustic codes.

  2. Hot gas ingestion testing of an advanced STOVL concept in the NASA Lewis 9- by 15-foot Low Speed Wind Tunnel with flow visualization

    Science.gov (United States)

    Johns, Albert L.; Flood, Joseph D.; Strock, Thomas W.; Amuedo, Kurt C.

    1988-01-01

    Advanced Short Takeoff/Vertical Landing (STOVL) aircraft capable of operating from remote sites, damaged runways, and small air capable ships are being pursued for deployment around the turn of the century. To achieve this goal, it is important that the technologies critical to this unique class of aircraft be developed. Recognizing this need, NASA Lewis Research Center, McDonnell Douglas Aircraft, and DARPA defined a cooperative program for testing in the NASA Lewis 9- by 15-foot Low Speed Wind Tunnel (LSWT) to establish a database for hot gas ingestion, one of the technologies critical to STOVL. Results from a test program are presented along with a discussion of the facility modifications allowing this type of testing at modal scale. These modifications to the tunnel include a novel ground plane, an elaborate model support which included 4 degrees of freedom, heated high pressure air for nozzle flow, a suction system exhaust for inlet flow, and tunnel sidewall modifications. Several flow visualization techniques were employed including water mist in the nozzle flows and tufts on the ground plane. Headwind (free-stream) velocity was varied from 8 to 23 knots.

  3. Investigation of Unsteady Tip Clearance Flow in a Low-Speed One and Half Stage Axial Compressor with LES And PIV

    Science.gov (United States)

    Hah, Chunill; Hathaway, Michael; Katz, Joseph; Tan, David

    2015-01-01

    The primary focus of this paper is to investigate how a rotor's unsteady tip clearance flow structure changes in a low speed one and half stage axial compressor when the rotor tip gap size is increased from 0.5 mm (0.49% of rotor tip blade chord, 2% of blade span) to 2.4 mm (2.34% chord, 4% span) at the design condition are investigated. The changes in unsteady tip clearance flow with the 0.62 % tip gap as the flow rate is reduced to near stall condition are also investigated. A Large Eddy Simulation (LES) is applied to calculate the unsteady flow field at these three flow conditions. Detailed Stereoscopic PIV (SPIV) measurements of the current flow fields were also performed at the Johns Hopkins University in a refractive index-matched test facility which renders the compressor blades and casing optically transparent. With this setup, the unsteady velocity field in the entire flow domain, including the flow inside the tip gap, can be measured. Unsteady tip clearance flow fields from LES are compared with the PIV measurements and both LES and PIV results are used to study changes in tip clearance flow structures. The current study shows that the tip clearance vortex is not a single structure as traditionally perceived. The tip clearance vortex is formed by multiple interlaced vorticities. Therefore, the tip clearance vortex is inherently unsteady. The multiple interlaced vortices never roll up to form a single structure. When phased-averaged, the tip clearance vortex appears as a single structure. When flow rate is reduced with the same tip gap, the tip clearance vortex rolls further upstream and the tip clearance vortex moves further radially inward and away from the suction side of the blade. When the tip gap size is increased at the design flow condition, the overall tip clearance vortex becomes stronger and it stays closer to the blade suction side and the vortex core extends all the way to the exit of the blade passage. Measured and calculated unsteady flow

  4. Simulation of the flow past a model in the closed test section of a low-speed wind tunnel and in the free stream

    Science.gov (United States)

    Bui, V. T.; Lapygin, V. I.

    2015-05-01

    The flow around a model in the closed test section of a low-speed wind tunnel has been analyzed in 2D approximation. As the contour of the nozzle, test section, and diffuser, the contour of the T-324 wind tunnel, of the Khristianovich Institute of Theoretical and Applied Mechanics (ITAM SB RAS, Novosibirsk), in its symmetry plane was adopted. A comparison of experimental with calculated data on the distribution of velocities and dynamic pressures in the test section is given. The effect due to the sizes of a model installed in the test section on the values of the aerodynamic coefficients of the model is analyzed. As the aerodynamic model, the NASA0012 airfoil and the circular cylinder were considered. For the airfoil chord length b = 20 % of nozzle height, the values of the aerodynamic coefficients of the airfoil in the free stream and in the test section proved to be close to each other up to the angle of attack a = 7°, which configuration corresponds to blockage-factor value ξ ≈ 7 %. The obtained data are indicative of the expedience of taking into account, in choosing the model scale, not only the degree of flow passage area blockage by the model but, also, the length of the well-streamlined model. In the case of a strongly blunted body with a high drag-coefficient value, the admissible blockage factor ξ may reach a value of 10 %.

  5. Hot gas ingestion test results of a two-poster vectored thrust concept with flow visualization in the NASA Lewis 9- x 15-foot low speed wind tunnel

    Science.gov (United States)

    Johns, Albert L.; Neiner, George; Bencic, Timothy J.; Flood, Joseph D.; Amuedo, Kurt C.; Strock, Thomas W.

    1990-01-01

    A 9.2 percent scale Short Takeoff and Vertical Landing (STOVL) hot gas ingestion model was designed and built by McDonnell Douglas Corporation (MCAIR) and tested in the Lewis Research Center 9 x 15 foot Low Speed Wind Tunnel (LSWT). Hot gas ingestion, the entrainment of heated engine exhaust into the inlet flow field, is a key development issure for advanced short takeoff and vertical landing aircraft. Flow visualization from the Phase 1 test program, which evaluated the hot ingestion phenomena and control techniques, is covered. The Phase 2 test program evaluated the hot gas ingestion phenomena at higher temperatures and used a laser sheet to investigate the flow field. Hot gas ingestion levels were measured for the several forward nozzle splay configurations and with flow control/life improvement devices (LIDs) which reduced the hot gas ingestion. The model support system had four degrees of freedom - pitch, roll, yaw, and vertical height variation. The model support system also provided heated high-pressure air for nozzle flow and a suction system exhaust for inlet flow. The test was conducted at full scale nozzle pressure ratios and inlet Mach numbers. Test and data analysis results from Phase 2 and flow visualization from both Phase 1 and 2 are documented. A description of the model and facility modifications is also provided. Headwind velocity was varied from 10 to 23 kn. Results are presented over a range of nozzle pressure ratios at a 10 kn headwind velocity. The Phase 2 program was conducted at exhaust nozzle temperatures up to 1460 R and utilized a sheet laser system for flow visualization of the model flow field in and out of ground effects. The results reported are for nozzle exhaust temperatures up to 1160 R. These results will contain the compressor face pressure and temperature distortions, the total pressure recovery, the inlet temperature rise, and the environmental effects of the hot gas. The environmental effects include the ground plane contours

  6. Consistent lattice Boltzmann modeling of low-speed isothermal flows at finite Knudsen numbers in slip-flow regime: Application to plane boundaries

    Science.gov (United States)

    Silva, Goncalo; Semiao, Viriato

    2017-07-01

    The first nonequilibrium effect experienced by gaseous flows in contact with solid surfaces is the slip-flow regime. While the classical hydrodynamic description holds valid in bulk, at boundaries the fluid-wall interactions must consider slip. In comparison to the standard no-slip Dirichlet condition, the case of slip formulates as a Robin-type condition for the fluid tangential velocity. This makes its numerical modeling a challenging task, particularly in complex geometries. In this work, this issue is handled with the lattice Boltzmann method (LBM), motivated by the similarities between the closure relations of the reflection-type boundary schemes equipping the LBM equation and the slip velocity condition established by slip-flow theory. Based on this analogy, we derive, as central result, the structure of the LBM boundary closure relation that is consistent with the second-order slip velocity condition, applicable to planar walls. Subsequently, three tasks are performed. First, we clarify the limitations of existing slip velocity LBM schemes, based on discrete analogs of kinetic theory fluid-wall interaction models. Second, we present improved slip velocity LBM boundary schemes, constructed directly at discrete level, by extending the multireflection framework to the slip-flow regime. Here, two classes of slip velocity LBM boundary schemes are considered: (i) linear slip schemes, which are local but retain some calibration requirements and/or operation limitations, (ii) parabolic slip schemes, which use a two-point implementation but guarantee the consistent prescription of the intended slip velocity condition, at arbitrary plane wall discretizations, further dispensing any numerical calibration procedure. Third and final, we verify the improvements of our proposed slip velocity LBM boundary schemes against existing ones. The numerical tests evaluate the ability of the slip schemes to exactly accommodate the steady Poiseuille channel flow solution, over

  7. Quantitative Infrared Image Analysis Of Simultaneous Upstream and Downstream Microgravity Flame Spread over Thermally-Thin Cellulose in Low Speed Forced Flow

    Science.gov (United States)

    Olson, S. L.; Lee, J. R.; Fujita, O.; Kikuchi, M.; Kashiwagi, T.

    2013-01-01

    The effect of low velocity forced flow on microgravity flame spread is examined using quantitative analysis of infrared video imaging. The objective of the quantitative analysis is to provide insight into the mechanisms of flame spread in microgravity where the flame is able to spread from a central location on the fuel surface, rather than from an edge. Surface view calibrated infrared images of ignition and flame spread over a thin cellulose fuel were obtained along with a color video of the surface view and color images of the edge view using 35 mm color film at 2 Hz. The cellulose fuel samples were mounted in the center of a 12 cm wide by 16 cm tall flow duct and were ignited in microgravity using a straight hot wire across the center of the 7.5 cm wide by 14 cm long samples. Four cases, at 1 atm. 35%O2 in N2, at forced flows from 2 cm/s to 20 cm/s are presented here. This flow range captures flame spread from strictly upstream spread at low flows, to predominantly downstream spread at high flow. Surface temperature profiles are evaluated as a function of time, and temperature gradients for upstream and downstream flame spread are measured. Flame spread rates from IR image data are compared to visible image spread rate data. IR blackbody temperatures are compared to surface thermocouple readings to evaluate the effective emissivity of the pyrolyzing surface. Preheat lengths and pyrolysis lengths are evaluated both upstream and downstream of the central ignition point. A surface energy balance estimates the net heat flux from the flame to the fuel surface along the length of the fuel. Surface radiative loss and gas-phase radiation from soot are measured relative to the net heat feedback from the flame. At high surface heat loss relative to heat feedback, the downstream flame spread does not occur.

  8. Low Speed Wind Tunnel Facility (LSWTF)

    Data.gov (United States)

    Federal Laboratory Consortium — Description: This facility consists of a large-scale, low-speed open-loop induction wind tunnel which has been modified to house a linear turbine cascade. A 125-hp...

  9. Hydrodynamical and magnetohydrodynamic global bifurcations in a highly turbulent von Karman flow; Bifurcations globales hydrodynamiques et magnetohydrodynamiques dans un ecoulement de von Karman turbulent

    Energy Technology Data Exchange (ETDEWEB)

    Ravelet, F

    2005-09-15

    We report experimental studies of the turbulent von Karman flow, inertially stirred between counter-rotating impellers. We first study the flow and its transition from laminar to turbulent regime. We highlight the role of slowly varying large scales, due to the presence of an azimuthal mixing layer. The large scales of this flow can be unstable in turbulent regime. We study the statistics of the transitions between the different mean states. The second part is dedicated to an experiment in liquid sodium, called VKS2. We optimize the time-averaged flow in order to allow kinematic dynamo action. We report the very first results of the experiment, and discuss the role of the large scales temporal non-stationariness. (author)

  10. Design of Through-flow Nacelle for Low-speed Wind Tunnel Testing of Civil Aircraft%民机低速风洞试验通气发房设计

    Institute of Scientific and Technical Information of China (English)

    胡仞与; 张东云; 施永毅

    2014-01-01

    通气发房是民机风洞试验中模拟发动机效应的一种有效手段。通过调整通气发房出口面积,可以对通过发房的流量进行控制,实现所需模拟的流量系数,保证进气流场的几何相似性。失速特性是民机的一个重要的性能指标,大量的低速风洞试验工作都着眼于着落构型下失速特性的研究;而在失速特性的适航审定试飞时的发动机将处于慢车功率状态,因此以模拟慢车流量系数作为低速风洞试验通气发房的设计目标,有助于在风洞试验中对失速特性进行预测。慢车功率时,由于发动机风扇压比很小,如保留外涵喷口形状,通气发房还能近似模拟风扇的喷流效应。发动机在慢车功率下的流量系数在0.5附近,为实现这一流量系数,在设计通气发房时,需调整内涵出口面积,使发房的总出口面积接近唇口面积的一半。 CFD计算证明这种设计方法得到的通气发房基本能够实现预期的流量系数。%Through-flow nacelle ( TFN) is an effective method of simulating engine effect in wind tunnel Testing. By adjusting the nozzle exit areas of a TFN, the flow passing the TFN could be controlled and the flow ratio ( MFR) could be achieved to make sure the similarity around the inlet flow field. As stall characteristics is one of the impor-tant factor in defining civil aircraft performance, a great portion of the low speed wind tunnel tests is devoted to the study of the stall characteristics of aircraft in landing configuration;and due to the fact that engines tend to be set at an idle condition during airworthy flight tests for stall speed determination, designing a TFN with a MFR corre-sponding to an idle power setting is desirable for the prediction of stall characteristics in wind tunnel testing. When running at idle conditions, an engine will have a very low fan pressure ratio, which means if the fan nozzle geometry is maintained, TFN can

  11. Application of fifth-order accurate HWCNS for low-speed complex flow field%五阶 HWCNS 在低速复杂流场中的应用

    Institute of Scientific and Technical Information of China (English)

    周云龙; 刘伟; 董义道; 王光学; 邓小刚

    2016-01-01

    采用五阶精度显式混合加权紧致非线性格式求解雷诺平均 NS 方程;利用多块对接结构网格技术,对30P -30N 多段翼型进行网格收敛性研究。在不考虑转捩的情况下,采用 SA 一方程湍流模型研究混合加权紧致非线性格式与二阶精度 MUSCL 格式对该翼型压力分布和典型站位速度型的影响,并与实验结果进行对比分析。采用混合加权紧致非线性格式和 SA 一方程湍流模型模拟梯形翼高升力构型低速复杂流场,通过对总体气动特性和压力分布的分析,探讨五阶精度显式混合加权紧致非线性格式在低速复杂外形流动中的应用能力。结果表明,对30P -30N 三段翼型,采用全湍流模拟方法可以得到较好的压力分布;对梯形翼高升力构型,在附着流和边界层小分离情况下混合加权紧致非线性格式有较好的模拟能力。%The fifth-order accurate explicit HWCNS(hybrid cell-edge and cell-node weighted compact nonlinear schemes)was used to solve Reynolds averaged Navier-Stokes equations.The grid convergence study of 30P -30N was performed by generating multi-block structured grids. The effects of HWCNS and the second-order accurate MUSCL on pressure distribution and velocity profiles at typical stations were studied using SA turbulence model without regarding transition,furthermore the numerical and experimental results were compared and analyzed.The trapezoidal wing was numerically simulated using HWCNS and SA turbulence model,and the application performance of HWCNS for low-speed complex configuration flows was discussed by analyzing the aerodynamic characters and the pressure distribution.Simulation results indicate that the pressure distribution of 30P -30N is simulated with the fully turbulent model accurately;as for the trapezoidal wing,HWCNS shows good simulation performance when dealing with the attached flow and small flow separation.

  12. Low Speed Automation, a French Initiative

    OpenAIRE

    Glaser, Sébastien; Cour, Maurice; NOUVELIERE, Lydie; LAMBERT, Alain; Nashashibi, Fawzi; Popieul, Jean-Christophe; Mourllion, Benjamin

    2012-01-01

    International audience; Nowadays, vehicle safety is constantly increasing thanks to the improvement of vehicle passive and active safety. However, on a daily usage of the car, traffic jams remains a problem. With limited space for road infrastructure, automation of the driving task on specific situation seems to be a possible solution. The French project ABV, which stands for low speed automation, tries to demonstrate the feasibility of the concept and to prove the benefits. In this article, ...

  13. Boundary-layer predictions for small low-speed contractions

    Science.gov (United States)

    Mehta, Rabindra D.; Bell, James H.

    1989-01-01

    The present scheme for the prediction of boundary-layer development in small, low-speed wind tunnel contraction sections proceeds by calculating the wall pressure distributions, and hence the wall velocity distributions, by means of a three-dimensional potential-flow method. For the family of contractions presently treated, the assumption of a laminar boundary layer appears to be justified; the measured boundary layer momentum thicknesses at the exit of the four contractions were found to lie within 10 percent of predicted values.

  14. Formation and evolution of a hairpin vortex induced by subharmonic sinuous low-speed streaks

    Energy Technology Data Exchange (ETDEWEB)

    Li, Jian; Dong, Gang; Lu, Ziheng, E-mail: dgvehicle@yahoo.com [State Key Laboratory of Transient Physics, Nanjing University of Science and Technology, Nanjing, 210094, Jiangsu Province, People’s Republic of China (China)

    2014-10-01

    In this paper, a process of the formation and evolution of hairpin vortices, which originated from the interaction between the spanwise-aligned low-speed streaks with a subharmonic sinuous (SS) oscillation mode, is studied using a direct numerical simulation method in a small periodic local region of an incompressible plane channel flow. The initial artificial perturbations are used to excite the SS-mode oscillation of two spanwise-aligned low-speed streaks in such a flow. A new mechanism of formation and decay of the hairpin vortices is proposed in which the shear layer induced by the spanwise collision and merging between the low-speed streaks is emphasized. Our results show that the streamwise vortices can be induced by the SS-mode streaks and then developed into an X-like pattern at the initial stage due to the mutual induction effect. The X-like vortices further enhance the spanwise oscillation and lift-up of the two streaks that thus lead to the spanwise collision and merging of the low-speed streaks and produce a low-speed region in high-speed fluid. The strong shear layer between the high- and low-speed fluids gives rise to the spanwise vorticity that connects the X-like streamwise vortices and forms the Λ-like vortex. Once the low-speed region entirely enters the high-speed fluid, the shear layer shows the ring shape and results in the transition from a Λ-like vortex to Ω-like one. After that, the viscous diffusion of the low-speed region in the high-speed fluid leads to the decay of the Ω-like vortex; the collision and merging of the low-speed streaks simultaneously reoccur upstream and give birth to a secondary Λ-like vortex, which exhibits behavior that is nearly similar with that of the primary one. Although the hairpin vortex packet is not observed in the present plane channel flow, the regeneration of the hairpin vortex suggests that this type of vortical structure plays an important role in the wall-bounded flow. (paper)

  15. Wind-tunnel investigation of the flow correction for a model-mounted angle of attack sensor at angles of attack from -10 deg to 110 deg. [Langley 12-foot low speed wind tunnel test

    Science.gov (United States)

    Moul, T. M.

    1979-01-01

    A preliminary wind tunnel investigation was undertaken to determine the flow correction for a vane angle of attack sensor over an angle of attack range from -10 deg to 110 deg. The sensor was mounted ahead of the wing on a 1/5 scale model of a general aviation airplane. It was shown that the flow correction was substantial, reaching about 15 deg at an angle of attack of 90 deg. The flow correction was found to increase as the sensor was moved closer to the wing or closer to the fuselage. The experimentally determined slope of the flow correction versus the measured angle of attack below the stall angle of attack agreed closely with the slope of flight data from a similar full scale airplane.

  16. 四级低速轴流压气机端壁区流动的实验研究%Experimental Studies of End-wall Flow in a Four-stage Low-speed Axial Compressor

    Institute of Scientific and Technical Information of China (English)

    张晨凯; 胡骏; 王志强

    2014-01-01

    Detailed flowfield measurements were made in the end-wall region of a four-stage low speed large-scare axial compressor test rig.Two ten-hole survey boundary layer probes,one four-hole-pneumatic probe,and several dynamic pressure probes each bedded with a high-frequency response Kulite sensor,were designed and manufactured to aid the test.Boundary layer region and mainflow region could be clearly distinguished from the boundary layer measurement results.A few parame-ters,including boundary layer thickness,displace thickness,momentum loss thickness,energy loss thickness and blockage coefficient were calculated based on the measurements.Results from turbulent boundary layer empirical formula of plate are in good agreement with the measurements,which indi-cates an excellent way of boundary layer effect estimation.Outlet flowfield of the third-stage rotor, measured by the displacement mechanism driven four-hole probe,shows that the lower end-wall boundary layer thickness is clearly smaller than that of the upper region,which can be contributed to the hub rotation.The evolution trajectory of TLV is identified evidently by dynamic pressure meas-urements.The maximum aerodynamic load point on the blade moves from the trailing to the leading edge as flowrate decreases,which leads to the forward movement of the tip leakage vortex inception point.%在四级低速大尺度轴流压气机试验台上,利用自行设计加工的十孔梳状附面层探针、四孔探针以及埋入高频响 Kulite 传感器的动态探针,针对端壁区流动展开了详细的流场测量。从附面层探针测量结果中能清晰识别出附面层区和主流区;获得了该压气机进口的附面层位移厚度、动量损失厚度、能量损失厚度及堵塞系数,且实验结果表明,采用平板紊流附面层公式能较好地进行附面层厚度的估算;采用位移机构带动四孔探针测得的第三级压气机转子进出口流场速度结果显示,受

  17. Low-speed Aerodynamic Investigations of a Hybrid Wing Body Configuration

    Science.gov (United States)

    Vicroy, Dan D.; Gatlin, Gregory M.; Jenkins, Luther N.; Murphy, Patrick C.; Carter, Melissa B.

    2014-01-01

    Two low-speed static wind tunnel tests and a water tunnel static and dynamic forced-motion test have been conducted on a hybrid wing-body (HWB) twinjet configuration. These tests, in addition to computational fluid dynamics (CFD) analysis, have provided a comprehensive dataset of the low-speed aerodynamic characteristics of this nonproprietary configuration. In addition to force and moment measurements, the tests included surface pressures, flow visualization, and off-body particle image velocimetry measurements. This paper will summarize the results of these tests and highlight the data that is available for code comparison or additional analysis.

  18. Effect of Fuselage and Tail Surfaces on Low-speed Yawing Characteristics of a Swept-wing Model as Determined in Curved-flow Test Section of Langley Stability Tunnel

    Science.gov (United States)

    Bird, John D; Jaquet, Byron M; Cowan, John W

    1951-01-01

    Results are presented of a wind-tunnel investigation made to determine the influence of the fuselage and tail surfaces on the rotary derivatives in yawing flight of a transonic-airplane configuration having 45 degrees sweptback wing and tail surfaces. The tests were run in the curved-flow test section of the Langley stability tunnel at a Reynolds number of 1.07 X 10 to the sixth power and consisted of balance measurements throughout the angle-of-attack range for several flight-path radii of curvature. The results are compared with data from forced-oscillation and free-oscillation tests, and a description of testing techniques used is included.

  19. Low-Speed Investigation of a Full-Span Internal-Flow Jet-Augmented Flap on a High-Wing Model with a 35 deg Swept Wing of Aspect Ratio 7.0

    Science.gov (United States)

    Turner, Thomas R.

    1960-01-01

    An investigation of a full-span 17-percent-chord internal-flow jet-augmented flap on an aspect-ratio-7.0 wing with 35 deg of sweepback has been made in the Langley 300-MPH 7- by 10-foot tunnel. Blowing over the conventional elevator and blowing down from a nose jet were investigated as a means of trimming the large diving moments at the high momentum and high lift coefficients. The results of the investigation showed that the model with the horizontal tail 0.928 mean aerodynamic chord above the wing-chord plane was stable to the maximum lift coefficient. The large diving-moment coefficients could be trimmed either with a downward blowing nose jet or by blowing over the elevator. Neither the downward blowing nose jet nor blowing over the elevator greatly affected the static longitudinal stability of the model. Trimmed lift coefficients up to 8.8 with blowing over the elevator and up to 11.4 with blowing down at the nose were obtained when the flap was deflected 70 deg and the total momentum coefficients were 3.26 and 4.69.

  20. Low speed axial compressor stall margin improvement by unsteady plasma actuation

    Science.gov (United States)

    Li, Gang; Xu, Yanji; Yang, Lingyuan; Du, Wei; Zhu, Junqiang; Nie, Chaoqun

    2014-04-01

    This research investigates the use of single dielectric barrier discharge (SDBD) actuators for energizing the tip leakage flow to suppress rotating stall inception and extend the stable operating range of a low speed axial compressor with a single rotor. The jet induced by the plasma actuator adds momentum to the flow in the tip region and has a significant impact on the tip-gap flow. Experiments are carried out on a low speed axial compressor with a single rotor. The static pressure is measured at both the rotor inlet and outlet. The flow coefficient and pressure rise coefficient are calculated. Then the characteristic line is acquired to show the overall performance of the compressor. With unsteady plasma actuation of 18kV and 60W the compressor stability range improvement is realized at rotor speed of 1500 r/min — 2400 r/min.

  1. Single Phase Permanent Magnet Low Speed Synchronous Motor

    Directory of Open Access Journals (Sweden)

    Gao Lianxue

    2013-04-01

    Full Text Available In order to acquire a better cognition to the single phase permanent magnet low speed synchronous motor and validate the correctness of the motor mathematical model, the performances of the motor are tested with the single phase permanent magnet low speed synchronous motor whose type is 70TDY4, the corresponding simulations are done too. The resistance and the inductance of the single phase permanent magnet low speed synchronous motor are measured. According to the data of experiments and simulations, the static characteristics of the single phase permanent magnet low speed synchronous motor with the changes of the phase shift resistance and the phase shift capacitance are analysed, the results of experiments and simulations prove the correctness of the mathematics model.

  2. Low-Speed Wind Tunnel Flow Quality Determination

    Science.gov (United States)

    2011-09-01

    Hot Wire Anemometry (HWA/CTA) System..................................17 a. Cable Length, S3...transducers. 5. Hot Wire Anemometry (HWA/CTA) System A Dantec Constant Temperature Anemometer (CTA) system comprised of three 56C01 CTA modules...component hot wire (CTA), the wall boundary layer characteristics consisting of the velocity profile, streamwise turbulence intensity, and spectral energy

  3. The application of the SAUNA CFD system to high and low speed vehicles

    Science.gov (United States)

    May, Nicholas E.; Peace, Andrew J.; Shaw, Jonathon A.

    1994-04-01

    The SAUNA grid generation and flow simulation system is applied to a variety of vehicles flows. The basic features and problems associated with predicting high speed external flows are discussed and contrasted with those associated with typical internal flows. Particular attention is paid in the discussion to turbulence modelling requirements. General descriptions of the grid generation philosophy adopted within the SAUNA system (structured, unstructured, hybrid) and the flow solution methodology are given. It is explained how the compressible flow algorithm may be modified to enable efficient calculation of low speed flows, thus extending the range of application of the SAUNA system to include conventional ground and sea vehicles. The grid generation capabilities of SAUNA are illustrated by showing examples of grids generated around configurations of a complete aircraft, a submarine and an automobile. The flow simulations are evaluated by comparison with experiment for several external high speed flows and a lower speed internal flow.

  4. Proactive condition monitoring of low-speed machines

    CERN Document Server

    Stamboliska, Zhaklina; Moczko, Przemyslaw

    2015-01-01

    This book broadens readers’ understanding of proactive condition monitoring of low-speed machines in heavy industries. It focuses on why low-speed machines are different than others and how maintenance of these machines should be implemented with particular attention. The authors explain the best available monitoring techniques for various equipment and the principle of how to get proactive information from each technique. They further put forward possible strategies for application of FEM for detection of faults and technical assessment of machinery. Implementation phases are described and industrial case-studies of proactive condition monitoring are included. Proactive Condition Monitoring of Low-Speed Machines is an essential resource for engineers and technical managers across a range of industries as well as design engineers working in industrial product development. This book also: ·         Explains the practice of proactive condition monitoring and illustrates implementation phases ·   ...

  5. Investigation of Load and Pressure Distribution onWing with Wake Rollup for Low Speed Aircraft

    OpenAIRE

    Laith W. Ismail

    2008-01-01

    The presented work shows a preliminary analytic method for estimation of load and pressure distributions on low speed wings with flow separation and wake rollup phenomenas. A higher order vortex panel method is coupled with the numerical lifting line theory by means of iterative procedure including models of separation and wake rollup. The computer programs are written in FORTRAN which are stable and efficient. The capability of the present method is investigated through a number of test case...

  6. EXPERIMENTAL INVESTIGATION OF ROTATING STALL FOR A LOW-SPEED CENTRIFUGAL COMPRESSOR

    Institute of Scientific and Technical Information of China (English)

    ZHU Xiaocheng; GUO Qiang; DU Zhaohui; CHEN Hua; ZHAO Yan

    2008-01-01

    Unsteady flows and rotating stall of a low-speed centrifugal compressor are investigated by measuring vaneless diffuser wall static pressure fluctuation and internal flow fields at different small flow fluxes. During the experiment, firstly the real time static pressure fluctuations on the vaneless diffuser shroud at different circumferential and radial position were acquired by high-frequency dynamic pressure transducers. Discrete Fourier transformation analysis and cross-correlation analysis were applied to the experimental results to ascertain the rotating stall beginning operation conditions and stall cells numbers and rotating speed. Secondly, the vaneless diffuser inlet flow angle distribution along diffuser width direction was acquired by single hotwire, which was compared with SENOO's analysis results. At last, the internal flow fields of the centrifugal compressor were investigated with a particle image velocimetry (PIV) system at different small flow fluxes. The flow field development of vaneless diffuser and blade flow passage are given at rotating stall conditions. The experiments enrich the understanding of rotating stall flow phenomenon of the low-speed centrifugal compressor and provide full experiment data for designing high performance centrifugal compressor.

  7. LUBRICATION FILM FORMATION MECHANISM OF SLIPPER PAIRS IN LOW SPEED HIGH TORQUE HYDRAULIC MOTORS

    Institute of Scientific and Technical Information of China (English)

    LI Yong; SHI Guanglin; CHEN Zhaoneng

    2007-01-01

    Pressure-flow analytical formulas of lubrication film of slipper pairs on camshaft connecting rod type low speed high torque (LSHT) hydraulic motors are put forward. The bottom surface of slipper pairs is rectangle, and the effect of squeeze flow and pressure differential flow is considered. The dynamic process of lubrication film formation through squeezing is numerically studied by computer simulation. Effects of supply pressure, initial lubrication film thickness, velocity damping coefficient, loading impact and gravity, etc are studied. Advantages of novel slipper pairs with large oil cavity area are pointed out.

  8. Application of Dual-blade Stator to Low-speed Ratio Performance Improvement of Torque Converters

    Institute of Scientific and Technical Information of China (English)

    WU Guangqiang; WANG Lijun

    2016-01-01

    With application of the lock-up clutch in the torque converter (TC), fuel economy is not much determined by its high-speed ratio transmission efficiency. As a benefit, more researches are focused on its low-speed ratio performance so as to improve vehicle gradeability and launching acceleration performance. According to the results of computational fluid dynamics (CFD) analysis, hydrodynamic loss inside the stator cascade accounts for 42% of the total energy loss at stalling speed ratio. It is found that upstream flow with large impingement angle results in boundary layer separation at the leading edge, which aggregates hydrodynamic loss and decreases circular flow rate dramatically at low-speed ratio. In this paper, a dual-blade stator is proposed to suppress the boundary layer separation, which is parameterized by using the non-uniform rational B spline (NURBS) method. The mean camber line and blade profile curve are expressed by a three control points quadratic open NURBS and a cubic closed one respectively. The key design parameters included the slot width and suction side shape of the primary blade are analyzed. The most effective slot width is found to be between 4% and 8% chord length, and the boundary layer separation can be suppressed completely by decreasing distribution of momentum moment at the primary blade and adding it to the leading edge of the secondary blade. As a result, circular flow rate and impeller torque capacity is increased by 17.9% and 9.6% respectively at stalling speed ratio, meanwhile, low-speed ratio efficiency is also improved. Maximum efficiency at high-speed ratio decreases by 0.5%, which can be ignored as the work of lock-up clutch. This research focuses on using the dual-blade stator to optimize low-speed ratio performance of the TC, which is benefit to vehicle power performance.

  9. Application of dual-blade stator to low-speed ratio performance improvement of torque converters

    Science.gov (United States)

    Wu, Guangqiang; Wang, Lijun

    2016-03-01

    With application of the lock-up clutch in the torque converter (TC), fuel economy is not much determined by its high-speed ratio transmission efficiency. As a benefit, more researches are focused on its low-speed ratio performance so as to improve vehicle gradeability and launching acceleration performance. According to the results of computational fluid dynamics (CFD) analysis, hydrodynamic loss inside the stator cascade accounts for 42% of the total energy loss at stalling speed ratio. It is found that upstream flow with large impingement angle results in boundary layer separation at the leading edge, which aggregates hydrodynamic loss and decreases circular flow rate dramatically at low-speed ratio. In this paper, a dual-blade stator is proposed to suppress the boundary layer separation, which is parameterized by using the non-uniform rational B spline (NURBS) method. The mean camber line and blade profile curve are expressed by a three control points quadratic open NURBS and a cubic closed one respectively. The key design parameters included the slot width and suction side shape of the primary blade are analyzed. The most effective slot width is found to be between 4% and 8% chord length, and the boundary layer separation can be suppressed completely by decreasing distribution of momentum moment at the primary blade and adding it to the leading edge of the secondary blade. As a result, circular flow rate and impeller torque capacity is increased by 17.9% and 9.6% respectively at stalling speed ratio, meanwhile, low-speed ratio efficiency is also improved. Maximum efficiency at high-speed ratio decreases by 0.5%, which can be ignored as the work of lock-up clutch. This research focuses on using the dual-blade stator to optimize low-speed ratio performance of the TC, which is benefit to vehicle power performance.

  10. Unstable phenomena of low speed compressible natural convection with open boundaries by multi-GPU implementation

    Science.gov (United States)

    Wang, Wei-Hsiang; Fu, Wu-Shung; Tsubokura, Makoto

    2016-11-01

    Unstable phenomena of low speed compressible natural convection are investigated numerically. Geometry contains parallel square plates or single heated plate with open boundaries is taken into consideration. Numerical methods of the Roe scheme, preconditioning and dual time stepping matching the DP-LUR method are used for low speed compressible flow. The absorbing boundary condition and modified LODI method is adopted to solve open boundary problems. High performance parallel computation is achieved by multi-GPU implementation with CUDA platform. The effects of natural convection by isothermal plates facing upwards in air is then carried out by the methods mentioned above Unstable behaviors appeared upon certain Rayleigh number with characteristic length respect to the width of plates or height between plates.

  11. Low Speed PSP Testing in Production Wind Tunnels

    Science.gov (United States)

    Bell, James; Mehta, Rabi; Schairer, Ed; Hand, Larry; Nixon, David (Technical Monitor)

    1998-01-01

    The brightness signal from a pressure-sensitive paint varies inversely with absolute pressure. Consequently high signal-to-noise ratios are required to resolve aerodynamic pressure fields at low speeds, where the pressure variation around an object might only be a few percent of the mean pressure. This requirement is unavoidable, and implies that care must be taken to minimize noise sources present in the measurement. This paper discusses and compares the main noise sources in low speed PSP testing using the "classical" intensity-based single-luminophore technique. These are: temperature variation, model deformation, and lamp drift/paint degradation. Minimization of these error sources from the point of view of operation in production wind tunnels is discussed, with some examples from recent tests in NASA Ames facilities.

  12. Modeling violent reaction following low speed impact on confined explosives

    Science.gov (United States)

    Curtis, John Philip; Jones, Andrew; Hughes, Christopher; Reaugh, John

    2012-03-01

    To ensure the safe storage and deployment of explosives it is important to understand the mechanisms that give rise to ignition and reaction growth in low speed impacts. The High Explosive Response to Mechanical Stimulus (HERMES) material model, integrated in the Lagrangian code LSDYNA, has been developed to model the progress of the reaction after such an impact. The low speed impact characteristics of an HMX based formulation have been examined using the AWE Steven Test. Axisymmetric simulations of an HMX explosive in the AWE Steven Test have been performed. A sensitivity study included the influence of friction, mesh resolution, and confinement. By comparing the experimental and calculated results, key model parameters which determine the explosive's response in this configuration have been identified. The model qualitatively predicts the point of ignition within the vehicle. Future refinements are discussed.

  13. Aeroacoustic response of coaxial wall-mounted Helmholtz resonators in a low-speed wind tunnel.

    Science.gov (United States)

    Slaton, William V; Nishikawa, Asami

    2015-01-01

    The aeroacoustic response of coaxial wall-mounted Helmholtz resonators with different neck geometries in a low-speed wind tunnel has been investigated. Experimental test results of this system reveal a strong aeroacoustic response over a Strouhal number range of 0.25 to 0.1 for both increasing and decreasing the flow rate in the wind tunnel. Aeroacoustic response in the low-amplitude range O(10(-3)) < Vac/Vflow < O(10(-1)) has been successfully modeled by describing-function analysis. This analysis, coupled with a turbulent flow velocity distribution model, gives reasonable values for the location in the flow of the undulating stream velocity that drives vortex shedding at the resonator mouth. Having an estimate for the stream velocity that drives the flow-excited resonance is crucial when employing the describing-function analysis to predict aeroacoustic response of resonators.

  14. PIV Measurements in the 14 x 22 Low Speed Tunnel: Recommendations for Future Testing

    Science.gov (United States)

    Watson, Ralph D.; Jenkins, Luther N.; Yao, Chung-Sheng; McGinley, Catherine B.; Paschal, Keith B.; Neuhart, Dan H.

    2003-01-01

    During the period from February 4 to March 21, 2003 stereo digital particle imaging velocimetry measurements were made on a generic high lift model, the Trap Wing, as part of the High Lift Flow Physics Experiment. These measurements were the first PIV measurements made in the NASA, Langley Research Center 14 x 22 Foot Low Speed Tunnel, and several problems were encountered and solved in the acquisition of the data. It is the purpose of this paper to document the solutions to these problems and to make recommendations for further improvements to the tunnel/setup in order to facilitate future measurements of this type.

  15. 9x15 Low Speed Wind Tunnel Improvements Update

    Science.gov (United States)

    Stephens, David

    2017-01-01

    The 9- by 15-Foot Low Speed Wind Tunnel (9x15 LSWT) at NASA Glenn Research Center was built in 1969 in the return leg of the 8- by 6-Foot Supersonic Wind Tunnel (8x6 SWT). The 9x15 LSWT was designed for performance testing of VSTOL aircraft models, but with the addition of the current acoustic treatment in 1986 the tunnel been used principally for acoustic and performance testing of aircraft propulsion systems. The present document describes an anticipated acoustic upgrade to be completed in 2018.

  16. Design and development of guide vane cascade for a low speed number Francis turbine

    Institute of Scientific and Technical Information of China (English)

    Biraj Singh THAPA; Chirag TRIVEDI; Ole Gunnar DAHLHAUG

    2016-01-01

    Guide vane cascade of a low speed number Francis turbine is developed for the experimental investigations. The test setup is able to produce similar velocity distributions at the runner inlet as that of a reference prototype turbine. Standard analytical methods are used to design the reference turbine. Periodic walls of flow channel between guide vanes are identified as the starting profile for the boundary of the cascade. Two alternative designs with three guide vanes and two guide vanes, without runner, are studied. A new approach, for the hydraulic design and optimization of the cascade test setup layout, is proposed and investigated in details. CFD based optimization methods are used to define the final layout of the test setup. The optimum design is developed as a test setup and experimental validation is done with PIV methods. The optimized design of cascade with one guide vane between two flow channels is found to produce similar flow conditions to that in the runner inlet of a low speed number Francis turbine.

  17. Development of Delta Wing Aerodynamics Research in Universiti Teknologi Malaysia Low Speed Wind Tunnel

    Directory of Open Access Journals (Sweden)

    Shabudin Mat

    2014-07-01

    Full Text Available This paper presents wind tunnel experiment on two delta wing configurations which are differentiated by their leading edge profiles: sharp and round-edged wings. The experiments were performed as a part of the delta wing aerodynamics research development in Universiti Teknologi Malaysia, low speed tunnel (UTM-LST. Steady load balance and flow visualization tests were conducted at Reynolds numbers of 0.5, 1, and 1.5 × 106, respectively. The flow measurement at low Reynolds number was also performed at as low as speed of 5 m/s. During the experiments, laser with smoke flow visualizations test was performed on both wings. The study has identified interesting features of the interrelationship between the conventional leading edge primary vortex and the occurrence and development of the vortex breakdown above the delta wings. The results conclude the vortex characteristics are largely dependent on the Reynolds number, angle of attack, and leading-edge radii of the wing.

  18. Numerical Simulation of a Complete Low-Speed Wind Tunnel Circuit

    Science.gov (United States)

    Nayani, Sudheer N.; Sellers, William L., III; Tinetti, Ana F.; Brynildsen, Scott E.; Walker, Eric L.

    2016-01-01

    A numerical simulation of the complete circuit of the NASA Langley 14 x 22-ft low-speed wind tunnel is described. Inside the circuit, all turning vanes are modeled as well as the five flow control vanes downstream of the 1st corner. The fan drive system is modeled using an actuator disk for the fan blades coupled with the fan nacelle. All the surfaces are modeled as viscous walls except the turning vanes, which were modeled as inviscid surfaces. NASA Langley's TetrUSS unstructured grid software was used for grid generation and flow simulation. Two turbulence models were employed in the present study, namely, the one-equation Spalart-Allmaras model and the shear stress transport (SST) model of Menter. The paper shows the flow characteristics in the circuit and compares the results with experimental data where available.

  19. Handling Qualities of Large Rotorcraft in Hover and Low Speed

    Science.gov (United States)

    Malpica, Carlos; Theodore, Colin R.; Lawrence , Ben; Blanken, Chris L.

    2015-01-01

    According to a number of system studies, large capacity advanced rotorcraft with a capability of high cruise speeds (approx.350 mph) as well as vertical and/or short take-off and landing (V/STOL) flight could alleviate anticipated air transportation capacity issues by making use of non-primary runways, taxiways, and aprons. These advanced aircraft pose a number of design challenges, as well as unknown issues in the flight control and handling qualities domains. A series of piloted simulation experiments have been conducted on the NASA Ames Research Center Vertical Motion Simulator (VMS) in recent years to systematically investigate the fundamental flight control and handling qualities issues associated with the characteristics of large rotorcraft, including tiltrotors, in hover and low-speed maneuvering.

  20. 9x15 Low Speed Wind Tunnel Acoustic Improvements

    Science.gov (United States)

    Stark, David; Stephens, David

    2016-01-01

    The 9- by 15-Foot Low Speed Wind Tunnel (9x15 LSWT) at NASA Glenn Research Center was built in 1969 in the return leg of the 8- by 6-Foot Supersonic Wind Tunnel (8x6 SWT). The 8x6 SWT was completed in 1949 and acoustically treated to mitigate community noise issues in 1950. This treatment included the addition of a large muffler downstream of the 8x6 SWT test section and diffuser. The 9x15 LSWT was designed for performance testing of VSTOL aircraft models, but with the addition of the current acoustic treatment in 1986 the tunnel has been used principally for acoustic and performance testing of aircraft propulsions systems. The present document describes an anticipated acoustic upgrade to be completed in 2017.

  1. Stagnation Region Heat Transfer Augmentation at Very High Turbulence Levels

    Energy Technology Data Exchange (ETDEWEB)

    Ames, Forrest [University of North Dakota; Kingery, Joseph E. [University of North Dakota

    2015-06-17

    A database for stagnation region heat transfer has been extended to include heat transfer measurements acquired downstream from a new high intensity turbulence generator. This work was motivated by gas turbine industry heat transfer designers who deal with heat transfer environments with increasing Reynolds numbers and very high turbulence levels. The new mock aero-combustor turbulence generator produces turbulence levels which average 17.4%, which is 37% higher than the older turbulence generator. The increased level of turbulence is caused by the reduced contraction ratio from the liner to the exit. Heat transfer measurements were acquired on two large cylindrical leading edge test surfaces having a four to one range in leading edge diameter (40.64 cm and 10.16 cm). Gandvarapu and Ames [1] previously acquired heat transfer measurements for six turbulence conditions including three grid conditions, two lower turbulence aero-combustor conditions, and a low turbulence condition. The data are documented and tabulated for an eight to one range in Reynolds numbers for each test surface with Reynolds numbers ranging from 62,500 to 500,000 for the large leading edge and 15,625 to 125,000 for the smaller leading edge. The data show augmentation levels of up to 136% in the stagnation region for the large leading edge. This heat transfer rate is an increase over the previous aero-combustor turbulence generator which had augmentation levels up to 110%. Note, the rate of increase in heat transfer augmentation decreases for the large cylindrical leading edge inferring only a limited level of turbulence intensification in the stagnation region. The smaller cylindrical leading edge shows more consistency with earlier stagnation region heat transfer results correlated on the TRL (Turbulence, Reynolds number, Length scale) parameter. The downstream regions of both test surfaces continue to accelerate the flow but at a much lower rate than the leading edge. Bypass transition occurs

  2. Oscillatory Behavior of an Arc Airfoil in Low-Speed Airflow

    Science.gov (United States)

    Molki, Majid; Sattari, Negin

    2011-11-01

    A computational investigation is conducted to study the oscillatory behavior of an arc airfoil situated in low-speed airflow. The present work is relevant to situations where the conventional rigid airfoils do not apply, such as the flight of bats. The outcome of this study is also beneficial in the design of micro air vehicles with flexible wings. The computations are performed using a deforming mesh to accommodate the airfoil oscillations. An unsteady, spatially second-order algorithm is employed to capture the time-variations of the lift and drag coefficients. A key feature of the present work is the flow response to airfoil oscillations. Fast Fourier Transform was applied to various parameters of the flow. For certain values of angle of attack for the non-oscillating airfoil, the flow has a dominant frequency and a well-defined vortex shedding. For other values of angle of attack, the flow around the non-oscillating airfoil contains many frequencies and has complex vortical structures. However, the oscillating airfoil in all cases makes the flow field periodic with well-defined patterns of vortex shedding. In this work, the flux of vorticity from the airfoil surface into the airflow is computed and compared with the pressure gradient along the surface of the airfoil. Effects of oscillations on magnitude and behavior of aerodynamic forces are also studied.

  3. Generation of atmospheric boundary layer in the IIUM low speed wind tunnel

    Science.gov (United States)

    Za'aba, Khalid Aldin Bin; Asrar, Waqar; Dheeb, Mohamad Al

    2017-03-01

    The purpose of this paper is to describe an attempt made to simulate the atmospheric boundary layer (ABL) in the Low Speed Wind Tunnel (LSWT) at IIUM. This was performed through modifications of the inlet and surface conditions of the test section. Devices such as spires, fences and surface roughness were used. The ASCE 7-10 standard was used as a reference to validate the results between the wind tunnel data and the full-scale ABL flow characteristics. The velocity profile and turbulence intensity were measured using a one-dimensional hotwire (CTA) probe. The data obtained show good agreement with ASCE 7-10 velocity profiles for exposures B and C while using a scale of 1:488 to match the wind tunnel data. The turbulence intensity profiles do not show a good agreement.

  4. Low-speed impact cratering in loose granular media

    Science.gov (United States)

    Durian, Douglas

    2005-03-01

    In this talk I shall describe the penetration of projectiles dropped into noncohesive granular media, and how the results vary with the properties of both the projectile and the medium. In contrast to wide assumption, the penetration depth and crater diameter represent two distinct length scales. The diameter scales as the 1/4 power of projectile energy, but curiously the depth is not a simple function of either the projectile energy or momentum at impact. Rather, it scales as the 1/2 power of density, the 2/3 power of projectile diameter, and the 1/3 power of total drop distance. This same result also holds for cylinders with a variety of tips, and so is not an accident of projectile shape. It is crucial to understand the penetration depth because it is directly related to the mechanics of impact, namely the average stopping force acting between projectile and medium. In addition to this discussion, I shall also present new data on the dynamics of impact. All experiments were constructed and carried out at UCLA by undergraduate physics majors: Jun Uehara, Katie Newhall, Chris Santore, and Mike Ambroso.[1] J.S. Uehara, M.A. Ambroso, R.P. Ojha, and D.J. Durian, ``Low-Speed Impact Craters in Loose Granular Media,'' Phys. Rev. Lett. 90, 194301 (2003).[2] K.A. Newhall and D.J. Durian, ``Projectile-shape dependence of impact craters in loose granular media,'' Phys. Rev. E 68, 06030R (2003).[3] M.A. Ambroso, C.R. Santore, A.R. Abate, and D.J. Durian, ``Penetration depth for shallow impact cratering,'' cond-mat/0411231 (2004).

  5. Low-speed flowfield characterization by infrared measurements of surface temperatures

    Science.gov (United States)

    Gartenberg, E.; Roberts, A. S., Jr.; Mcree, G. J.

    1989-01-01

    An experimental program was aimed at identifying areas in low speed aerodynamic research where infrared imaging systems can make significant contributions. Implementing a new technique, a long electrically heated wire was placed across a laminar jet. By measuring the temperature distribution along the wire with the IR imaging camera, the flow behavior was identified. Furthermore, using Nusselt number correlations, the velocity distribution could be deduced. The same approach was used to survey wakes behind cylinders in a wind-tunnel. This method is suited to investigate flows with position dependent velocities, e.g., boundary layers, confined flows, jets, wakes, and shear layers. It was found that the IR imaging camera cannot accurately track high gradient temperature fields. A correlation procedure was devised to account for this limitation. Other wind-tunnel experiments included tracking the development of the laminar boundary layer over a warmed flat plate by measuring the chordwise temperature distribution. This technique was applied also to the flow downstream from a rearward facing step. Finally, the IR imaging system was used to study boundary layer behavior over an airfoil at angles of attack from zero up to separation. The results were confirmed with tufts observable both visually and with the IR imaging camera.

  6. Measurement and analysis of radiated sound from a low speed fan with a large tip gap.

    Science.gov (United States)

    Bilka, M J; Anthoine, J; Schram, C

    2014-05-01

    The wake flow field and radiated sound from a low speed axial fan is studied experimentally. The fan geometry uses controlled diffusion blades and is designed with a low aspect ratio (0.9). The fan is installed with a large tip gap, approximately 10% of the blade span. The radiated sound field is analyzed using a known trailing edge noise formulation. First, the model is compared to an experiment of a single airfoil in a wind tunnel to assess the predictive capabilities. Second, measurements of the fan are made at two different blade loading conditions. Hot wire measurements are made in the near wake of the fan to assess the extent of the tip leakage flow for each condition. The radiated sound fields are compared with the trailing edge noise theory. Use is made of the wake measurements as an input to a surface pressure model. When the fan is operated with the optimal blade loading, the influence of the tip leakage flow is found to be of secondary acoustic impact. When the fan is operated at a high loading condition for the blades, a more significant leakage flow develops and is found to be responsible for the dominant radiated sound.

  7. Low Speed Motion Optimization of Space Manipulator Based on Gradient Projection Method

    Directory of Open Access Journals (Sweden)

    Peng Junjie

    2015-01-01

    Full Text Available Low-speed crawling phenomenon may occur when space manipulators run at a low speed, which may bring big problem for manipulation work. A kind of low-speed optimization algorithm based on gradient projection method is pro-posed in this paper. The designing of continuous balanced proportional factor can effectively reduce the quantitative differences between the homogeneous solution and the special solution, avoiding the joint velocities oscillations. The low-speed crawling problem can be effectively improved by appropriate increase of joint velocities. And the effectiveness and correctness of the optimization algorithm are confirmed by the simulation.

  8. Investigation of Load and Pressure Distribution onWing with Wake Rollup for Low Speed Aircraft

    Directory of Open Access Journals (Sweden)

    Laith W. Ismail

    2008-01-01

    Full Text Available The presented work shows a preliminary analytic method for estimation of load and pressure distributions on low speed wings with flow separation and wake rollup phenomena’s. A higher order vortex panel method is coupled with the numerical lifting line theory by means of iterative procedure including models of separation and wake rollup. The computer programs are written in FORTRAN which are stable and efficient. The capability of the present method is investigated through a number of test cases with different types of wing sections (NACA 0012 and GA(W-1 for different aspect ratios and angles of attack, the results include the lift and drag curves, lift and pressure distributions along the wing span taking into the consideration the effect of the angles of attack and the aspect ratios on the wake rollup. The pressure distribution on the wings shows that there is a region of constant pressure on the upper surface of the wings near the trailing edge in the middle of the wing, also there is a region of flow separation on the upper surface of the wings. A good agreement is found between the presented work results and other from previous researches. These results show that the presented method is able to capture much of flow over wings feature like separation and wake rollup.

  9. Low-speed aerodynamic characteristics of a powered NASP-like configuration in ground effect

    Science.gov (United States)

    Gatlin, Gregory M.

    1989-01-01

    Results are presented on the low-speed aerodynamic characteristics of a simplified NASP (for National Aerospace Plane Program)-like configuration, obtained in the NASA-Langley 14-by-22-foot subsonic tunnel. The model consisted of a triangular wedge forebody, a rectangular midsection housing the propulsion simulation system, and a rectangular wedge aftbody; it also included a delta wing, exhaust flow deflectors, and aftbody fences. Flow visualization was obtained by injecting water into the engine simulator inlets and using a laser light sheet to illuminate the resulting exhaust flow. It was found that power-on ground effects for NASP-like configuration can be substantial; these effects can be reduced by increasing the angle-of-attack to the value of the aftbody ramp angle. Power-on lift losses in ground effect increased with increasing thrust, but could be reduced by the addition of a delta wing to the configuration. Power-on lift losses also increased with use of aftbody fences.

  10. Experimental Research on an Active Sting Damper in a Low Speed Acoustic Wind Tunnel

    Directory of Open Access Journals (Sweden)

    Jinjin Chen

    2014-01-01

    Full Text Available Wind tunnels usually use long cantilever stings to support aerodynamic models in order to reduce support system flow interference on experimental data. However, such support systems are a potential source of vibration problems which limit the test envelope and affect data quality due to the inherently low structural damping of the systems. When exposed to tunnel flow, turbulence and model flow separation excite resonant Eigenmodes of a sting structure causing large vibrations due to low damping. This paper details the development and experimental evaluation of an active damping system using piezoelectric devices with balance signal feedback both in a lab and a low speed acoustic wind tunnel and presents the control algorithm verification tests with a simple cantilever beam. It is shown that the active damper, controlled separately by both PID and BP neural network, has effectively attenuated the vibration. For sting mode only, 95% reduction of displacement response under exciter stimulation and 98% energy elimination of sting mode frequency have been achieved.

  11. STEADY STATE PERFORMANCES ANALYSIS OF MODERN MARINE TWO-STROKE LOW SPEED DIESEL ENGINE USING MLP NEURAL NETWORK MODEL

    Directory of Open Access Journals (Sweden)

    Ozren Bukovac

    2016-01-01

    Full Text Available Compared to the other marine engines for ship propulsion, turbocharged two-stroke low speed diesel engines have advantages due to their high efficiency and reliability. Modern low speed ”intelligent” marine diesel engines have a flexibility in its operation due to the variable fuel injection strategy and management of the exhaust valve drive. This paper carried out verified zerodimensional numerical simulations which have been used for MLP (Multilayer Perceptron neural network predictions of marine two-stroke low speed diesel engine steady state performances. The developed MLP neural network was used for marine engine optimized operation control. The paper presents an example of achieving lowest specific fuel consumption and for minimization of the cylinder process highest temperature for reducing NOx emission. Also, the developed neural network was used to achieve optimal exhaust gases heat flow for utilization. The obtained data maps give insight into the optimal working areas of simulated marine diesel engine, depending on the selected start of the fuel injection (SOI and the time of the exhaust valve opening (EVO.

  12. Testing of Lightweight Fuel Cell Vehicles System at Low Speeds with Energy Efficiency Analysis

    Science.gov (United States)

    Mustaffa, Muhammad Rizuwan B.; Mohamed, Wan Ahmad Najmi B. Wan

    2013-12-01

    A fuel cell vehicle power train mini test bench was developed which consists of a 1 kW open cathode hydrogen fuel cell, electric motor, wheel, gearing system, DC/DC converter and vehicle control system (VCS). Energy efficiency identification and energy flow evaluation is a useful tool in identifying a detail performance of each component and sub-systems in a fuel cell vehicle system configuration. Three artificial traction loads was simulated at 30 kg, 40 kg and 50 kg force on a single wheel drive configuration. The wheel speed range reported here covers from idle to 16 km/h (low speed range) as a preliminary input in the research work frame. The test result shows that the system efficiency is 84.5 percent when the energy flow is considered from the fuel cell to the wheel and 279 watts of electrical power was produced by the fuel cell during that time. Dynamic system responses was also identified as the load increases beyond the motor traction capabilities where the losses at the converter and motor controller increased significantly as it tries to meet the motor traction power demands. This work is currently being further expanded within the work frame of developing a road-worthy fuel cell vehicle.

  13. Sub-harmonic broadband humps and tip noise in low-speed ring fans.

    Science.gov (United States)

    Moreau, Stéphane; Sanjose, Marlène

    2016-01-01

    A joint experimental and numerical study has been achieved on a low-speed axial ring fan in clean inflow. Experimental evidence shows large periodic broadband humps at lower frequencies than the blade passing frequencies and harmonics even at design conditions. These sub-harmonic humps are also found to be sensitive to the fan process and consequently to its tip geometry. Softer fans yield more intense humps more shifted to lower frequencies with respect to the fan harmonics. Unsteady turbulent flow simulations of this ring fan mounted on a test plenum have been achieved by four different methods that have been validated by comparing with overall performances and detailed hot-wire velocity measurements in the wake. Noise predictions are either obtained directly or are obtained through Ffowcs Williams and Hawkings' analogy, and compared with narrowband and third-octave power spectra. All unsteady simulations correctly capture the low flow rates, the coherent vortex dynamics in the tip clearance and consequently the noise radiation dominated by the tip noise in the low- to mid-frequency range. Yet, only the scale-adaptive simulation and the lattice Boltzmann method simulations which can describe most of the turbulent structures accurately provide the proper spectral shape and levels, and consequently the overall sound power level.

  14. The Response of a Low Speed Compressor on Rotating Inlet Distortion

    Institute of Scientific and Technical Information of China (English)

    Chaoqun NIE; Jingxuan ZHANG; Zhiting TONG; Hongwu ZHANG

    2006-01-01

    In multi-spool engines,the downstream compressor experiences a rotating inlet distortion if rotating stall occurs in upstream compressor,which may induce the instability of the whole compressor.In this paper,the compressor dynamic behavior is the major focus.The experiment was carried out on a single-stage low-speed axial-flow compressor.A rotating distortion generator equipped with different distortion sector(s) was designed to produce different rotating inlet distortion clockwise or counterclockwise with up to 100% of the compressor design speed.The distortion sector can be installed single or in some combination such as four sectors together.Three types of distortion sector/combination are used in the research work,which are single 30 degree sector,four 30 degree sectors and single 120 degree sector.It is found that the total pressure loss caused by rotating sector(s) increases when the distortion speed rises.For co-rotating distortions,all the three types of inlet distortion exhibited a peak in stall margin degradation when the distortion speed corresponded to roughly 50% of rotor speed.The two-dimensional numerical simulations of the compressor flow field clearly show the propagation of the disturbances trigged by the distortion sector(s).

  15. Performance Improvement of Servo Machine Low Speed Operation Using RBFN Disturbance Observer

    DEFF Research Database (Denmark)

    Lee, Kyo-Beum; Blaabjerg, Frede

    2004-01-01

    A new scheme to estimate the moment of inertia in the servo motor drive system in very low speed is proposed in this paper. The typical speed estimation scheme in most servo system for low speed operation is sensitive to the variation of machine parameters, especially the moment of inertia....... To estimate the motor inertia value, the observer using the Radial Basis Function Networks (RBFN) is applied. The effectiveness of the proposed inertia estimation method is verified by experiments. It is concluded that the speed control performance in the low speed region is improved with the proposed...

  16. Polarization of radiation of electrons in highly turbulent magnetic fields

    Science.gov (United States)

    Prosekin, A. Yu.; Kelner, S. R.; Aharonian, F. A.

    2016-09-01

    We study the polarization properties of the jitter and synchrotron radiation produced by electrons in highly turbulent anisotropic magnetic fields. The net polarization is provided by the geometry of the magnetic field the directions of which are parallel to a certain plane. Such conditions may appear in the relativistic shocks during the amplification of the magnetic field through the so-called Weibel instability. While the polarization properties of the jitter radiation allows extraction of direct information on the turbulence spectrum as well as the geometry of magnetic field, the polarization of the synchrotron radiation reflects the distribution of the magnetic field over its strength. For the isotropic distribution of monoenergetic electrons, we found that the degree of polarization of the synchrotron radiation is larger than the polarization of the jitter radiation. For the power-law energy distribution of electrons the relation between the degree of polarization of synchrotron and jitter radiation depends on the spectral index of the distribution.

  17. Polarization of radiation of electrons in highly turbulent magnetic fields

    CERN Document Server

    Prosekin, A Yu; Aharonian, F A

    2016-01-01

    We study the polarization properties of the jitter and synchrotron radiation produced by electrons in highly turbulent anisotropic magnetic fields. The net polarization is provided by the geometry of the magnetic field the directions of which are parallel to a certain plane. Such conditions may appear in the relativistic shocks during the amplification of the magnetic field through the so-called Weibel instability. While the polarization properties of the jitter radiation allows extraction of direct information on the turbulence spectrum as well as the geometry of magnetic field, the polarization of the synchrotron radiation reflects the distribution of the magnetic field over its strength. For the isotropic distribution of monoenergetic electrons, we found that the degree of polarization of the synchrotron radiation is larger than the polarization of the jitter radiation. For the power-law energy distribution of electrons the relation between the degree of polarization of synchrotron and jitter radiation dep...

  18. Design of a Low Speed Fan Stage for Noise Suppression

    Science.gov (United States)

    Dalton, W. N.; Elliot, D. B.; Nickols, K. L.

    1999-01-01

    This report describes the design of a low tip speed, moderate pressure rise fan stage for demonstration of noise reduction concepts. The fan rotor is a fixed-pitch configuration delivering a design pressure ratio of 1.378 at a specific flow of 43.1 lbm/sec/sq ft. Four exit stator configurations were provided to demonstrate the effectiveness of circumferential and axial sweep in reducing rotor-stator interaction tone noise. The fan stage design was combined with an axisymmetric inlet, conical convergent nozzle, and nacelle to form a powered fan-nacelle subscale model. This model has a 22-inch cylindrical flow path and employs a rotor with a 0.30 hub-to-tip radius ratio. The design is fully compatible with an existing NASA force balance and rig drive system. The stage aerodynamic and structural design is described in detail. Three-dimensional (3-D) computational fluid dynamics (CFD) tools were used to define optimum airfoil sections for both the rotor and stators. A fan noise predictive system developed by Pratt & Whitney under contract to NASA was used to determine the acoustic characteristics of the various stator configurations. Parameters varied included rotor-to-stator spacing and vane leading edge sweep. The structural analysis of the rotor and stator are described herein. An integral blade and disk configuration was selected for the rotor. Analysis confirmed adequate low cycle fatigue life, vibratory endurance strength, and aeroelastic suitability. A unique load carrying stator arrangement was selected to minimize generation of tonal noise due to sources other than rotor-stator interaction. Analysis of all static structural components demonstrated adequate strength, fatigue life, and vibratory characteristics.

  19. Small Propeller and Rotor Testing Capabilities of the NASA Langley Low Speed Aeroacoustic Wind Tunnel

    Science.gov (United States)

    Zawodny, Nikolas S.; Haskin, Henry H.

    2017-01-01

    The Low Speed Aeroacoustic Wind Tunnel (LSAWT) at NASA Langley Research Center has recently undergone a configuration change. This change incorporates an inlet nozzle extension meant to serve the dual purposes of achieving lower free-stream velocities as well as a larger core flow region. The LSAWT, part of the NASA Langley Jet Noise Laboratory, had historically been utilized to simulate realistic forward flight conditions of commercial and military aircraft engines in an anechoic environment. The facility was modified starting in 2016 in order to expand its capabilities for the aerodynamic and acoustic testing of small propeller and unmanned aircraft system (UAS) rotor configurations. This paper describes the modifications made to the facility, its current aerodynamic and acoustic capabilities, the propeller and UAS rotor-vehicle configurations to be tested, and some preliminary predictions and experimental data for isolated propeller and UAS rotor con figurations, respectively. Isolated propeller simulations have been performed spanning a range of advance ratios to identify the theoretical propeller operational limits of the LSAWT. Performance and acoustic measurements of an isolated UAS rotor in hover conditions are found to compare favorably with previously measured data in an anechoic chamber and blade element-based acoustic predictions.

  20. Robust and Stable Disturbance Observer of Servo System for Low-Speed Operation

    DEFF Research Database (Denmark)

    Lee, Kyo Beum; Blaabjerg, Frede

    2007-01-01

    A new scheme to estimate the moment of inertia in the servo motor drive system in very low speed is proposed in this paper. The speed estimation scheme in most servo drive systems for low-speed operation is sensitive to the variation of machine parameter, especially the moment of inertia. To esti......A new scheme to estimate the moment of inertia in the servo motor drive system in very low speed is proposed in this paper. The speed estimation scheme in most servo drive systems for low-speed operation is sensitive to the variation of machine parameter, especially the moment of inertia....... To estimate the motor inertia value, the observer using the Radial Basis Function Network (RBFN) is applied. A control law for stabilizing the system and adaptive laws for updating both of the weights in the RBFN and a bounding constant are established so that the whole closed-loop system is stable...

  1. The design and analysis of simple low speed flap systems with the aid of linearized theory computer programs

    Science.gov (United States)

    Carlson, Harry W.

    1985-01-01

    The purpose here is to show how two linearized theory computer programs in combination may be used for the design of low speed wing flap systems capable of high levels of aerodynamic efficiency. A fundamental premise of the study is that high levels of aerodynamic performance for flap systems can be achieved only if the flow about the wing remains predominantly attached. Based on this premise, a wing design program is used to provide idealized attached flow camber surfaces from which candidate flap systems may be derived, and, in a following step, a wing evaluation program is used to provide estimates of the aerodynamic performance of the candidate systems. Design strategies and techniques that may be employed are illustrated through a series of examples. Applicability of the numerical methods to the analysis of a representative flap system (although not a system designed by the process described here) is demonstrated in a comparison with experimental data.

  2. Waveless ships in the low speed limit: Results for multi-cornered hulls

    CERN Document Server

    Trinh, Philippe H

    2015-01-01

    In the low-speed limit, a blunt ship modeled as two-dimensional semi-infinite body with a single corner can never be made waveless. This was the conclusion of the previous part of our work in Trinh et al. (2011), which focused on the Dagan & Tulin (1972) model of ship waves in the low speed limit. In this accompanying paper, we continue our investigations with the study of more general, piecewise-linear, or multi-cornered ships. The low-speed or low-Froude limit, coupled with techniques in exponential asymptotics allows us to derive explicit formulae relating the geometry of the hull to the form of the waves. Configurations with closely spaced corners present a non-trivial extension of the theory, and we present the general methodology for their study. Lastly, numerical computations of the nonlinear ship-wave problem are presented in order to confirm the analytical predictions.

  3. A Very Low-Speed Sensorless Induction Motor Drive with Online Stator Resistance identification scheme

    Directory of Open Access Journals (Sweden)

    M. Zaky

    2008-03-01

    Full Text Available Recently, speed sensorless control of induction motor drives received great attention to avoid the different problems associated with direct speed sensors. However, low speed operation with robustness against parameter variations remains an area of research for sensorless systems. Stator resistance is of greatest importance for good operation of speed sensorless systems in low speed region. In this paper, a sliding mode current observer for an induction motor is presented. An estimation algorithm based on this observer in conjunction with Popov's hyper-stability theory is proposed to calculate the speed and stator resistance independently. The proposed speed observer with parallel stator resistance identification is firstly verified by simulation. Experimental results are included as well to demonstrate the good performance of the proposed observer and estimation algorithms at low speed.

  4. Sensitivity Analysis of Heavy Fuel Oil Spray and Combustion under Low-Speed Marine Engine-Like Conditions

    Directory of Open Access Journals (Sweden)

    Lei Zhou

    2017-08-01

    Full Text Available On account of their high power, thermal efficiency, good reliability, safety, and durability, low-speed two-stroke marine diesel engines are used as the main drive devices for large fuel and cargo ships. Most marine engines use heavy fuel oil (HFO as the primary fuel, however, the physical and chemical characteristics of HFO are not clear because of its complex thermophysical properties. The present study was conducted to investigate the effects of fuel properties on the spray and combustion characteristics under two-stroke marine engine-like conditions via a sensitivity analysis. The sensitivity analysis of fuel properties for non-reacting and reacting simulations are conducted by comparing two fuels having different physical properties, such as fuel density, dynamic viscosity, critical temperature, and surface tension. The performances of the fuels are comprehensively studied under different ambient pressures, ambient temperatures, fuel temperatures, and swirl flow conditions. From the results of non-reacting simulations of HFO and diesel fuel properties in a constant volume combustion chamber, it can be found that the increase of the ambient pressure promotes fuel evaporation, resulting in a reduction in the steady liquid penetration of both diesel and HFO; however, the difference in the vapor penetrations of HFO and diesel reduces. Increasing the swirl flow significantly influences the atomization of both HFO and diesel, especially the liquid distribution of diesel. It is also found that the ambient temperature and fuel temperature have the negative effects on Sauter mean diameter (SMD distribution. For low-speed marine engines, the combustion performance of HFO is not sensitive to activation energy in a certain range of activation energy. At higher engine speed, the difference in the effects of different activation energies on the in-cylinder pressure increases. The swirl flow in the cylinder can significantly promote fuel evaporation and

  5. Turbulence Measurements in Swirling Flows

    Directory of Open Access Journals (Sweden)

    V. M. Domkundwar

    1981-10-01

    Full Text Available Investigation have been conducted to find out the region of high turbulent intensities in a swirling jet passing through a divergent passage. A hot wire anemometer is used to measure the turbulence intensity using a four position method. It has been concluded that the jet spreads with increasing diffuser angle and the region of high turbulent intensity also spreads. The high turbulence intensity region lies around the recirculation zone and it decays rapidly along the main flow direction.

  6. A low-speed wind tunnel study of vortex interaction control techniques on a chine-forebody/delta-wing configuration

    Science.gov (United States)

    Rao, Dhanvada M.; Bhat, M. K.

    1992-01-01

    A low speed wind tunnel evaluation was conducted of passive and active techniques proposed as a means to impede the interaction of forebody chine and delta wing vortices, when such interaction leads to undesirable aerodynamic characteristics particularly in the post stall regime. The passive method was based on physically disconnecting the chine/wing junction; the active technique employed deflection of inboard leading edge flaps. In either case, the intent was to forcibly shed the chine vortices before they encountered the downwash of wing vortices. Flow visualizations, wing pressures, and six component force/moment measurements confirmed the benefits of forced vortex de-coupling at post stall angles of attack and in sideslip, viz., alleviation of post stall zero beta asymmetry, lateral instability and twin tail buffet, with insignificant loss of maximum lift.

  7. 40 CFR 205.54-1 - Low speed sound emission test procedures.

    Science.gov (United States)

    2010-07-01

    ... 40 Protection of Environment 24 2010-07-01 2010-07-01 false Low speed sound emission test procedures. 205.54-1 Section 205.54-1 Protection of Environment ENVIRONMENTAL PROTECTION AGENCY (CONTINUED... example, temperature, humidity, and barometric pressure). (ii) Proper signal levels, terminat-ing...

  8. Experimental Testing of a Generic Submarine Model in the DSTO Low Speed Wind Tunnel. Phase 2

    Science.gov (United States)

    2014-03-01

    Defence Science and Technology Organisation Technical Report DSTO-TR-1622, 2004. [3] Barlow, J. B., Rae , W. H. and Pope, A., Low-Speed Wind Tunnel...kW (900 hp) electric motor driving a 3.96 m diameter eight bladed fan, with a maximum rotational speed 750 RPM, manually controlled. Cooling 40 °C

  9. Film thickness of mechanically worked lubricating grease at very low speeds

    NARCIS (Netherlands)

    Cen, H.; Lugt, Pieter Martin; Morales-Espejel, G.E.

    2014-01-01

    Several different types of commercially available greases, aged in a roll stability tester, have been tested in a ball-on-disc machine where the film thickness was measured using the interferometry method. The grease film thickness at very low speed is thicker than the base oil film thickness due to

  10. Evaluation of spray drift using low speed wind tunnel measurements and dispersion modeling

    Science.gov (United States)

    The objective of this work was to evaluate the EPA’s proposed Test Plan for the validation testing of pesticide spray drift reduction technologies (DRTs) for row and field crops, focusing on the evaluation of ground application systems using the low-speed wind tunnel protocols and processing the dat...

  11. Low speed hybrid generalized predictive control of a gasoline-propelled car.

    Science.gov (United States)

    Romero, M; de Madrid, A P; Mañoso, C; Milanés, V

    2015-07-01

    Low-speed driving in traffic jams causes significant pollution and wasted time for commuters. Additionally, from the passengers׳ standpoint, this is an uncomfortable, stressful and tedious scene that is suitable to be automated. The highly nonlinear dynamics of car engines at low-speed turn its automation in a complex problem that still remains as unsolved. Considering the hybrid nature of the vehicle longitudinal control at low-speed, constantly switching between throttle and brake pedal actions, hybrid control is a good candidate to solve this problem. This work presents the analytical formulation of a hybrid predictive controller for automated low-speed driving. It takes advantage of valuable characteristics supplied by predictive control strategies both for compensating un-modeled dynamics and for keeping passengers security and comfort analytically by means of the treatment of constraints. The proposed controller was implemented in a gas-propelled vehicle to experimentally validate the adopted solution. To this end, different scenarios were analyzed varying road layouts and vehicle speeds within a private test track. The production vehicle is a commercial Citroën C3 Pluriel which has been modified to automatically act over its throttle and brake pedals.

  12. On Modeling Structural Excitations by Low Speed Turbulent Boundary Layer Flows

    Science.gov (United States)

    2003-08-01

    Corcos cross- spectral density function is recommended since no known cross- spectral density function can be obtained to express the inverse Fourier...the cross- spectral density function , is also frequently used. For an infinite plate, analyses were performed in the wavenumber-frequency domain via the...directly from the integration of the triple product of the TBL cross- spectral density function and two eigenfunctions each of which specifies the

  13. Upwind scheme for acoustic disturbances generated by low-speed flows

    DEFF Research Database (Denmark)

    Ekaterinaris, J.A.

    1997-01-01

    , compressible how equations, A numerical method for the solution of the equations governing the acoustic field is presented. The primitive variable form of the governing equations is used for the numerical solution. Time integration is performed with a fourth-order, Runge-Kutta method, Discretization...

  14. Development and Application of an Advanced Optical Based Pressure Instrument for Low-Speed Flows.

    Science.gov (United States)

    2007-11-02

    and paint photodegradation . In the conventional approach, errors associated with these effects are minimized by relating pressure to the ratio of a...da*pcr electron configuration), strongly luminesces in the 511-517 nm region with the quantum yield of 0.52 approaching that of laser dyes [2]. The

  15. Effects of very high turbulence on convective heat transfer

    Science.gov (United States)

    Moffat, R. J.; Maciejewski, P. K.

    1984-01-01

    The effects of high-intensity, large-scale turbulence on turbulent boundary-layer heat transfer are studied. Flow fields were produced with turbulence intensities up to 40% and length scales up to several times the boundary layer thickness. In addition, three different types of turbulence will be compared to see whether they have the same effect on the boundary layer. The three are: the far field of a free jet, flow downstream of a grid, and flow downstream of a simulated gas turbine combustor. Each turbulence field will be characterized by several measures: intensity (by component), scale, and spectrum. Heat transfer will be measured on a 2.5 m long, 0.5 m wide flat plate using the energy-balance technique. The same plate will be used in each of the four flow fields; a low-turbulence tunnel for baseline data, and the three flow situations mentioned.

  16. Non-linear backstepping control of five-phase IM drive at low speed conditions-experimental implementation.

    Science.gov (United States)

    Echeikh, Hamdi; Trabelsi, Ramzi; Iqbal, Atif; Bianchi, Nicola; Mimouni, Mohamed Fouizi

    2016-11-01

    In this paper non-linear backstepping control (BSC) is employed for high performance five-phase induction motor drive for low speed operation. The traditional control approaches such as direct torque control and indirect rotor field oriented control introduces stability problem at low speed. The proposed BSC is shown to offer stable operation in the sense of Lyapunov and high dynamics at low speed. Experimental results are provided to present the proprieties of the proposed approach at low speed in terms of stability, torque ripple, desired control performance, achievable dynamics and complexity of implementation etc. Copyright © 2016. Published by Elsevier Ltd.

  17. An Application of CFD to Guide Forced Boundary-Layer Transition for Low-Speed Tests of a Hybrid Wing-Body Configuration

    Science.gov (United States)

    Luckring, James M.; Deere, Karen A.; Childs, Robert E.; Stremel, Paul M.; Long, Kurtis R.

    2016-01-01

    A hybrid transition trip-dot sizing and placement test technique was developed in support of recent experimental research on a hybrid wing-body configuration under study for the NASA Environmentally Responsible Aviation project. The approach combines traditional methods with Computational Fluid Dynamics. The application had three-dimensional boundary layers that were simulated with either fully turbulent or transitional flow models using established Reynolds-Averaged Navier-Stokes methods. Trip strip effectiveness was verified experimentally using infrared thermography during a low-speed wind tunnel test. Although the work was performed on one specific configuration, the process was based on fundamental flow physics and could be applicable to other configurations.

  18. Fluid Flow Characterization of High Turbulent Intensity Compressible Flow Using Particle Image Velocimetry

    Science.gov (United States)

    2015-08-01

    archive, University of St Andrews. [8] Cengel Yunus A., Cimbala John M., “Fluid Mechanics: Fundamentals and Applications, McGraw-Hill”, 2006 [9...Gas Dynamics”, Pearson Prentice Hall, 2006 [25] Dynalene Inc., HC series data sheet, accessed 2014 [26] Cengel Y. A., “Heat and Mass Transfer

  19. Longitudinal Acceleration Tracking Control of Low Speed Heavy-Duty Vehicles

    Institute of Scientific and Technical Information of China (English)

    WANG Yuejian; BIN Yang; LI Keqiang

    2008-01-01

    This paper presents a model matching control (MMC) method based on the sliding mode control(SMC) method for longitudinal acceleration tracking control in a vehicular stop-and-go cruise control system.The nonlinearity of the vehicle acceleration response at low speeds was analyzed to develop a transfer function model of the vehicle longitudinal dynamics using the least-mean-square system identification technique.This transfer function was then used to design the MMC controller,including an SMC feedback compensator.The system combines the advantages of the two control methods with robust control and rapid response.Simulations show that the controller enhances the rapid trackability to the vehicle acceleration and improves the system's robustness at low speeds compared with conventional PID MMC controllers.

  20. SOME CHARACTERISTICS OF LOW-SPEED STREAKS UNDER SHEARED AIR-WATER INTERFACES

    Institute of Scientific and Technical Information of China (English)

    王双峰; 贾复

    2001-01-01

    The characteristics of low-speed fluid streaks occurring under sheared air-water interfaces were examined by means of hydrogen bubble visualization tech nique. A critical shear condition under which the streaky structure first appears was determined to be uT ≈ 0.19 cm/s. The mean spanwise streak spacing increases with distance from the water surface owing to merging and bursting processes, and a lin ear relationship describing variation of non-dimensional spacing λ+- versus y+ was found essentially independent of shear stress on the interface. Values ofλ+, however,are remarkably smaller than their counterparts in the near-wall region of turbulent boundary layers. Though low-speed streaks occur randomly in time and space, the streak spacing exhibits a lognormal probability distribution behavior. A tentative explanation concerning the formation of streaky structure is suggested, and the fact that λ+ takes rather smaller values than that in wall turbulence is briefly discussed.

  1. A learning-based autonomous driver: emulate human driver's intelligence in low-speed car following

    Science.gov (United States)

    Wei, Junqing; Dolan, John M.; Litkouhi, Bakhtiar

    2010-04-01

    In this paper, an offline learning mechanism based on the genetic algorithm is proposed for autonomous vehicles to emulate human driver behaviors. The autonomous driving ability is implemented based on a Prediction- and Cost function-Based algorithm (PCB). PCB is designed to emulate a human driver's decision process, which is modeled as traffic scenario prediction and evaluation. This paper focuses on using a learning algorithm to optimize PCB with very limited training data, so that PCB can have the ability to predict and evaluate traffic scenarios similarly to human drivers. 80 seconds of human driving data was collected in low-speed (car-following scenarios. In the low-speed car-following tests, PCB was able to perform more human-like carfollowing after learning. A more general 120 kilometer-long simulation showed that PCB performs robustly even in scenarios that are not part of the training set.

  2. The Effects of Fuels and Lubricants on Low- Speed Pre- Ignition in Gasoline SI Engines

    Institute of Scientific and Technical Information of China (English)

    Eric LIU

    2012-01-01

    With the onset of downsized and highly- boosted engines, engine designers are encountering a new combustion phenomenon, called low - speed pre - ignition (LSPI) or superknock, which occurs when the engine operates under a low - speed, high - load conditions. LSPI events cause large spikes in cylinder pressure that can easily exceed the design limits of the engine. Therefore, it is important for the automotive industry to understand how LSPI events occur and develop a so- lution that can either eliminate it or detect and mitigate its effects. This paper summarizes the existing work that has been conducted on the subject of LSPI. Much of presented hypothesizes that physical and chemical interactions and accumulation of fuels and lubricants in crevice volume affect the frequency of LPSl events. Therefore, it may be possible to formulate fuels and mitigate or eliminate the occurrence of LPSI. the research work the piston top land lubricants that can

  3. Computer simulations and experimental study on crash box of automobile in low speed collision

    Science.gov (United States)

    Liu, Yanjie; Ding, Lin; Yan, Shengyuan; Yang, Yongsheng

    2008-11-01

    Based on the problems of energy-absorbing components in the automobile low speed collision process, according to crash box frontal crash test in low speed as the example, the simulation analysis of crash box impact process was carried out by Hyper Mesh and LS-DYNA. Each parameter on the influence modeling was analyzed by mathematics analytical solution and test comparison, which guaranteed that the model was accurate. Combination of experiment and simulation result had determined the weakness part of crash box structure crashworthiness aspect, and improvement method of crash box crashworthiness was discussed. Through numerical simulation of the impact process of automobile crash box, the obtained analysis result was used to optimize the design of crash box. It was helpful to improve the vehicles structure and decrease the collision accident loss at most. And it was also provided a useful method for the further research on the automobile collision.

  4. Sensorless Characteristics of Hybrid PM Machines at Zero and Low Speed

    DEFF Research Database (Denmark)

    Matzen, Torben N.; Rasmussen, Peter Omand

    2009-01-01

    for analysing the suitability for sensorless control at zero and low speed. The method can be used to evaluate a particular machine design so the self-sensing characteristics for sensorless control of machine can be found. The characteristics can be obtained from finite element simulation data or experimental......Sensorless methods for zero and low speed operation in drives with hybrid PM machines make use of the machine saliency to determine the rotor position in an indirect fashion. When integrating the position measurement in the electrical power supply to the machine, i.e. make the machine self......-sensing, the sensorless obtained position can be affected by the actual operation conditions of the machine e.g. the stator currents. This may deteriorate the machine self-sensing suitability using injection methods. In this paper an analysis method based on accurate knowledge of the machine flux linkages is proposed...

  5. A Study of Slipper and Rail Wear Interaction at Low Speed

    Science.gov (United States)

    2014-06-19

    taking care of the boys, a house and a dog and for not getting discouraged. I pray that they will learn as I have how important it is to ensure Yahovah...wear, delamination wear, seizure wear, melt wear, severe oxidational wear and adhesive wear. Adhesive wear comprised of three zones: low speed...model is experiencing seizure or melt wear, then something is wrong with the model. Lim and Ashby also published on their wear map the normalized wear

  6. Temperature change in pig rib bone during implant site preparation by low-speed drilling

    Directory of Open Access Journals (Sweden)

    Sun-Jong Kim

    2010-10-01

    Full Text Available OBJECTIVES: The purpose of this study was to evaluate the temperature change during low-speed drilling using infrared thermography. MATERIAL AND METHODS: Pig ribs were used to provide cortical bone of a similar quality to human mandible. Heat production by three implant drill systems (two conventional drilling systems and one low-speed drilling system was evaluated by measuring the bone temperature using infrared thermography. Each system had two different bur sizes. The drill systems used were twist drill (2.0 mm/2.5 mm, which establishes the direction of the implant, and finally a 3.0 mm-pilot drill. Thermal images were recorded using the IRI1001 system (Infrared Integrated Systems Ltd.. Baseline temperature was 31±1ºC. Measurements were repeated 10 times, and a static load of 10 kg was applied while drilling. Data were analyzed using descriptive statistics. Statistical analysis was conducted with two-way ANOVA. RESULTS AND CONCLUSIONS: Mean values (n=10 drill sequences for maximum recorded temperature (Max TºC, change in temperature (ΔTºC from baseline were as follows. The changes in temperature (ΔTºC were 1.57ºC and 2.46ºC for the lowest and the highest values, respectively. Drilling at 50 rpm without irrigation did not produce overheating. There was no significant difference in heat production between the 3 implant drill systems (p>0.05. No implant drill system produced heat exceeding 47ºC, which is the critical temperature for bone necrosis during low-speed drilling. Low-speed drilling without irrigation could be used during implant site preparation.

  7. Reconstruction of Low Speed Rear-End collisions - Technical Means of Assessing Cervical Spine Injuries

    Directory of Open Access Journals (Sweden)

    Martin Hitzemann

    2003-01-01

    Full Text Available In recent years, an increasing number of cervical spine injuries sustained by vehicle occupants in collisions at comparatively low speeds have been reported to insurance companies and in civil litigation. The reported injuries occur in both rear-end and side impact collisions. The paper describes how a detailed assessment of such cases requires interdisciplinary teamwork involving technical, biomechanical and medical experts.

  8. Hysteresis zone or locus - Aerodynamic of bulbous based bodies at low speeds

    Science.gov (United States)

    Covert, E. E.

    1979-01-01

    Experimental data are presented which seem to suggest that a well-defined hysteresis locus on bulbous based bodies at low speeds does not exist. Instead, if the experiment is repeated several times, the entire hysteresis region seems to fill with data rather than trace out a specific hysteresis locus. Data obtained on an oscillating model even at low reduced frequencies may be well defined but when applied to arbitrary motion lead to less accurate results than desired.

  9. Research on the low speed stability control technology of fly-cutting machine for KDP crystals

    Science.gov (United States)

    Chen, Dongsheng; Ji, Fang; Chen, Hua

    2014-08-01

    In the paper, The problem about stability in low speed of the air bearing stage driven by a linear motor was investigated to satisfy the ultra-precision fly-cutting of KDP crystals. First of all, the modal of the servo system with the permanent magnet synchronous linear motor was analyzed. In the system of the low speed linear motor driver, the main interferences came from cutting force f Load , the friction of chain and cable f n , the ripple thrust f ripp , and motor friction f fric . Secondly, the factors about low speed stability were analyzed: the key to improve the system's stability is to control the interference forces; Another important issue is to develop an advanced control strategy. Thirdly, some optimization experiments about low speed stability were developed as follows: the influence of feedback element, the influence of Power converter, speed optimization of damping feed-forward control, speed optimization of Spindle vibration, speed optimization based on disturbance observer. Finally the experimental results: the lowest speed of the stage can reach 0.2 mm/min; the error of the speed is less than 0.06mm/min when running between 1mm/min and 10 mm/min. The cutting experiment of KDP with the size of 330mm × 330mm × 10mm, was proceeded on the Fly-cutting machine by the feeding velocity of 1mm/min. The results about the surface roughness show that the value of Rq is 3.3nm and the value of Ra is 2.6nm.

  10. Gravitationally defined velocities for a low speed hot-wire calibration

    Science.gov (United States)

    Haw, R. C.; Ali, S. K.; Foss, J. F.

    1987-01-01

    A technique to provide the reference velocity for a low speed hot-wire calibration is described. A pivoted arm falls under the action of gravity and the resulting velocity field can be used to define the transfer function coefficients in a modified Collis and Williams (1959) relationship. In nominal agreement with a published result, a deviation from this relationship for a film Reynolds number such that Re exp n of less than about 0.24 is observed.

  11. Very-low speed control of PMSM based on EKF estimation with closed loop optimized parameters.

    Science.gov (United States)

    Xu, Dong; Zhang, Shaoguang; Liu, Jingmeng

    2013-11-01

    When calculating the speed from the position of permanent magnet synchronous motor (PMSM), the accuracy and real-time are limited by the precision of the sensor. This problem causes crawling and jitter at very-low speed. Using the angle from the position sensor, an extended Kalman filter (EKF) designed in dq-coordinate is presented to solve this problem. The usage of position sensor simplifies the model and improves the accuracy of speed estimation. Specially, a closed loop optimal (CLO) method is devised to overcome the difficulty to adjust the parameters of the EKF. The EKF is the feedback link of speed control, CLO method is derived from the perspective of the speed step response to optimize the measurement covariance matrix and the system covariance matrix of EKF. Simulation and experimental results, comparing the low-speed performance of the EKF and sensor feedback methods, prove the effectiveness of the method to adjust the parameters of EKF and the advantages in eliminating the low speed jitter.

  12. Acoustic emission-based condition monitoring methods: Review and application for low speed slew bearing

    Science.gov (United States)

    Caesarendra, Wahyu; Kosasih, Buyung; Tieu, Anh Kiet; Zhu, Hongtao; Moodie, Craig A. S.; Zhu, Qiang

    2016-05-01

    This paper presents an acoustic emission-based method for the condition monitoring of low speed reversible slew bearings. Several acoustic emission (AE) hit parameters as the monitoring parameters for the detection of impending failure of slew bearings are reviewed first. The review focuses on: (1) the application of AE in typical rolling element bearings running at different speed classifications, i.e. high speed (>600 rpm), low speed (10-600 rpm) and very low speed (<10 rpm); (2) the commonly used AE hit parameters in rolling element bearings and (3) AE signal processing, feature extraction and pattern recognition methods. In the experiment, impending failure of the slew bearing was detected by the AE hit parameters after the new bearing had run continuously for approximately 15 months. The slew bearing was then dismantled and the evidence of the early defect was analysed. Based on the result, we propose a feature extraction method of the AE waveform signal using the largest Lyapunov exponent (LLE) algorithm and demonstrate that the LLE feature can detect the sign of failure earlier than the AE hit parameters with improved prediction of the progressive trend of the defect.

  13. Disturbance observer that uses radial basis function networks for the low speed control of a servo motor

    DEFF Research Database (Denmark)

    Lee, Kyo-Beum; Bae, C.H.; Blaabjerg, Frede

    2005-01-01

    A scheme to estimate the moment of inertia in a servo motor drive system at very low speed is proposed. The typical speed estimation scheme used in most servo systems operated at low speed is highly sensitive to variations in the moment of inertia. An observer that uses a radial basis function ne...

  14. Position-and Velocity- Sensorless Control of Cylindrical Brushless DC Motors Driven by Sinusoidal Current at Low Speed Using Eddy Current

    Science.gov (United States)

    Takashima, Hiroshi; Tomita, Mutuwo; Chen, Zhiqian; Satoh, Mitsuhiko; Doki, Shinji; Okuma, Shigeru

    This paper proposes to paste non-magnetic materials on the rotor surface of a cylindrical brushless DC motor and to use the model including the extended e.m.f. for sensorless control. In the proposed method, the inductance changes depending on the rotor position because of eddy currents, which flow on the non-magnetic material at high frequency. The rotor position can be estimated at standstill and at low speeds. The simulation results show that the proposed method is very useful.

  15. Minimum-Voltage Vector Injection Method for Sensorless Control of PMSM for Low-Speed Operations

    DEFF Research Database (Denmark)

    Xie, Ge; Lu, Kaiyuan; Kumar, Dwivedi Sanjeet

    2016-01-01

    In this paper, a simple signal injection method is proposed for sensorless control of PMSM at low speed, which ideally requires one voltage vector only for position estimation. The proposed method is easy to implement resulting in low computation burden. No filters are needed for extracting...... may also be further developed to inject two opposite voltage vectors to reduce the effects of inverter voltage error on the position estimation accuracy. The effectiveness of the proposed method is demonstrated by comparing with other sensorless control method. Theoretical analysis and experimental...

  16. Status of The General Atomics Low Speed Urban Maglev Technology Development Program

    Energy Technology Data Exchange (ETDEWEB)

    Gurol, S; Baldi, R; Bever, D; Post, R

    2004-06-16

    This paper presents the status of General Atomics Urban Maglev Program. The development provides an innovative approach for low speed transportation suitable for very challenging urban environments. Permanent magnets arranged in a 'Halbach' array configuration produce a relatively stiff magnetic suspension operating with an air gap of 25 mm. The project has progressed from design and prototype hardware testing, to the construction of a 120-meter full-scale test track, located in San Diego, California. Dynamic testing of the levitation, propulsion and guidance systems is being performed.

  17. The Acoustic Environment of the NASA Glenn 9- by 15-foot Low-Speed Wind Tunnel

    Science.gov (United States)

    Stephens, David B.

    2015-01-01

    The 9- by 15-Foot Low Speed Wind Tunnel is an acoustic testing facility with a long history of aircraft propulsion noise research. Due to interest in renovating the facility to support future testing of advanced quiet engine designs, a study was conducted to document the background noise level in the facility and investigate the sources of contaminating noise. The anechoic quality of the facility was also investigated using an interrupted noise method. The present report discusses these aspects of the noise environment in this facility.

  18. Electromyography responses of pediatric and young adult volunteers in low-speed frontal impacts.

    Science.gov (United States)

    Mathews, Emily A; Balasubramanian, Sriram; Seacrist, Thomas; Maltese, Matthew R; Sterner, Robert; Arbogast, Kristy B

    2013-10-01

    No electromyography (EMG) responses data exist of children exposed to dynamic impacts similar to automotive crashes, thereby, limiting active musculature representation in computational occupant biomechanics models. This study measured the surface EMG responses of three neck, one torso and one lower extremity muscles during low-speed frontal impact sled tests (average maximum acceleration: 3.8g; rise time: 58.2ms) performed on seated, restrained pediatric (n=11, 8-14years) and young adult (n=9, 18-30years) male subjects. The timing and magnitude of the EMG responses were compared between the two age groups. Two normalization techniques were separately implemented and evaluated: maximum voluntary EMG (MVE) and neck cross-sectional area (CSA). The MVE-normalized EMG data indicated a positive correlation with age in the rectus femoris for EMG latency; there was no correlation with age for peak EMG amplitudes for the evaluated muscles. The cervical paraspinous exhibited shorter latencies compared with the other muscles (2-143ms). Overall, the erector spinae and rectus femoris peak amplitudes were relatively small. Neck CSA-normalized peak EMG amplitudes negatively correlated with age for the cervical paraspinous and sternocleidomastoid. These data can be useful to incorporate active musculature in computational models, though it may not need to be age-specific in low-speed loading environments.

  19. Experimental investigation about the effect of non-axisymmetric wake impact on a low speed axial compressor

    Science.gov (United States)

    Liu, Jianyong; Lu, Yajun; Li, Zhiping

    2010-05-01

    Non-axisymmetric wake impact experiments were carried out after the best exciting frequency for a low speed axial compressor had been found by axisymmetric wake impact experiments. When the number and circumferential distribution of inlet guide vanes (IGV) are logical the wakes of non-axisymmetric IGVs can exert beneficial unsteady exciting effect on their downstream rotor flow fields and improve the compressor’s performance. In the present paper, four non-axisymmetric wake impact plans were found working better than the axisymmetric wake impact plan. Compared with the base plan, the best non-axisymmetric plan increased the compressor’s peak efficiency, and the total pressure rise by 1.1 and 2%, and enhanced the stall margin by 4.4%. The main reason why non-axisymmetric plans worked better than the axisymmetric plan was explained as the change of the unsteady exciting signal arising from IGV wakes. Besides the high-frequency components, the non-axisymmetric plan generated a beneficial low-frequency square-wave exciting signal and other secondary frequency components. Compared with the axisymmetric plan, multi-frequency exciting wakes arising from the non-axisymmetric plans are easier to get coupling relation with complex vortices such as clearance vortices, passage vortices and shedding vortices.

  20. Robust and Stable Disturbance Observer of Servo System for Low Speed Operation Using the Radial Basis Function Network

    DEFF Research Database (Denmark)

    Lee, Kyo-Beum; Blaabjerg, Frede

    2005-01-01

    A new scheme to estimate the moment of inertia in the servo motor drive system in very low speed is proposed in this paper. The speed estimation scheme in most servo drive systems for low speed operation is sensitive to the variation of machine parameter, especially the moment of inertia. To esti......A new scheme to estimate the moment of inertia in the servo motor drive system in very low speed is proposed in this paper. The speed estimation scheme in most servo drive systems for low speed operation is sensitive to the variation of machine parameter, especially the moment of inertia....... To estimate the motor inertia value, the observer using the Radial Basis Function Network (RBFN) is applied. A control law for stabilizing the system and adaptive laws for updating both of the weights in the RBFN and a bounding constant are established so that the whole closed-loop system is stable...

  1. 9- by 15-Foot Low Speed Wind Tunnel Acoustic Improvements Expanded Overview

    Science.gov (United States)

    Stephens, David

    2016-01-01

    The 9- by 15-Foot Low Speed Wind Tunnel (9x15 LSWT) at NASA Glenn Research Center was built in 1969 in the return leg of the 8- by 6-Foot Supersonic Wind Tunnel (8x6 SWT). The 8x6 SWT was completed in 1949 and acoustically treated to mitigate community noise issues in 1950. This treatment included the addition of a large muffler downstream of the 8x6 SWT test section and diffuser. The 9x15 LSWT was designed for performance testing of V/STOL aircraft models, but with the addition of the current acoustic treatment in 1986 the tunnel been used principally for acoustic and performance testing of aircraft propulsion systems. The present document describes an anticipated acoustic upgrade to be completed in 2017.

  2. Impact characteristics of a vehicle population in low speed front to rear collisions.

    Science.gov (United States)

    Nishimura, Naoya; Simms, Ciaran K; Wood, Denis P

    2015-06-01

    Rear impact collisions are mostly low severity, but carry a very high societal cost due to reported symptoms of whiplash and related soft tissue injuries. Given the difficulty in physiological measurement of damage in whiplash patients, there is a significant need to assess rear impact severity on the basis of vehicle damage. This paper presents fundamental impact equations on the basis of an equivalent single vehicle to rigid barrier collision in order to predict relationships between impact speed, maximum dynamic crush, mean and peak acceleration, time to common velocity and vehicle stiffness. These are then applied in regression analysis of published staged low speed rear impact tests. The equivalent mean and peak accelerations are linear functions of the collision closing speed, while the time to common velocity is independent of the collision closing speed. Furthermore, the time to common velocity can be used as a surrogate measure of the normalized vehicle stiffness, which provides opportunity for future accident reconstruction.

  3. High Turbulence

    CERN Multimedia

    EuHIT, Collaboration

    2015-01-01

    As a member of the EuHIT (European High-Performance Infrastructures in Turbulence - see here) consortium, CERN is participating in fundamental research on turbulence phenomena. To this end, the Laboratory provides European researchers with a cryogenic research infrastructure (see here), where the first tests have just been performed.

  4. Study of the post-derailment safety measures on low-speed derailment tests

    Science.gov (United States)

    Guo, Lirong; Wang, Kaiyun; Lin, Jianhui; Zhang, Bing; Chen, Zaigang; Song, Xinwu; Du, Gaofeng

    2016-07-01

    Prevention of train from derailment is the most important issue for the railway system. Keeping derailed vehicle close to the track centreline is beneficial to minimise the severe consequences associated with derailments. In this paper, the post-derailment safety measures are studied based on low-speed derailment tests. Post-derailment devices can prevent deviation of the train from the rail by catching the rail, and they are mounted under the axle box. Considering the different structures of vehicles, both trailer and motor vehicles are equipped with the safety device and then separately used in low-speed derailment tests. In derailment tests, two kinds of track, namely the CRTS-I slab ballastless track and the CRTS-II bi-block sleeper ballastless track, are adopted to investigate the effect of the track types on the derailment. In addition, the derailment speed and the weight of the derailed vehicle are also taken into account in derailment tests. The test results indicate that the post-derailment movement of the vehicle includes running and bounce. Reducing the derailment speed and increasing the weight of the head of the train are helpful to reduce the possibility for derailments. For the CRTS-I slab ballastless track, the safety device can prevent trailer vehicles from deviating from the track centreline. The gearbox plays an important role in controlling the lateral displacement of motor vehicle after a derailment while the safety device contributes less to keep derailed motor vehicles on the track centreline. The lateral distance between the safety device and rails should be larger than 181.5 mm for protecting the fasteners system. And for the CRTS-II bi-block sleeper ballastless track, it helps to decrease the post-derailment distance due to the longitudinal impacts with sleepers. It can also restrict the lateral movement of derailed vehicle due to the high shoulders. The results suggest that, CRTS-II bi-block sleeper ballastless track should be widely used

  5. Optimizing Low Speed VoIP Network for Rural Next Generation Network (R-NGN

    Directory of Open Access Journals (Sweden)

    Yoanes Bandung

    2007-11-01

    Full Text Available In this research, we propose an optimization method based-on E-Model for designing an efficient low speed VoIP network for Rural Next Generation Network (R-NGN. We are choosing 128 kbps and 256 kbps bandwidth as the typical community link to be used in the designing of R-NGN infrastructure. The method is based on selection of some VoIP network parameters such as voice coder, communication protocol, packet loss level, network utilization and resource allocation. We draw analytic approach for achieving rating value (R of E-model that represent level of quality of service. In this approach, we focus on delay and packet loss calculation to find the rating value. We state the rating value = 70 as minimum level of quality of service for each call, equivalent to 3.6 of Mean Opinion Score (MOS. In our experiments, either G.723.1 5.3 kbps or G.729 is chosen for maximizing the number of VoIP calls, it depends on link utilization and level of packet loss.

  6. Binocular videogrammetric system for three-dimensional measurement in low-speed wind tunnel

    Science.gov (United States)

    Zhu, Ye; Gu, Yonggang; Zhai, Chao

    2014-11-01

    In order to avoid the defects of contact measurement, such as limited range, complex constructing and disability of 3-D parameter acquisition, we built a binocular videogrammetric system for measuring 3-D geometry parameters of wind tunnel test models, for instance, displacement, rotation angle and vibration, in low-speed wind tunnel. The system is based on the principles of close-range digital photogrammetry. As a non-contact system, it acquires parameters without interference in the experiments, and it has adjustable range and simple structure. It is worth mentioning that this is a Realtime measurement system, so that it can greatly compress the experiment period, furthermore, it is also able to provide some specific experiments with parameters for online adjustment. In this system, images are acquired through two industrial digital cameras and a PCI-E image acquisition card, and they are processed in a PC. The two cameras are triggered by signals come from a function signal generator, so that images of different cameras will have good temporal synchronization to ensure the accuracy of 3-D reconstruction. A two-step stereo calibration technique using planar pattern developed by Zhengyou Zhang is used to calibrate these cameras. Results of wind tunnel test indicate that the system can provide displacement accuracy better than 0.1% and rotation angle accuracy better than 0.1 degree, besides, the vibration frequency accuracy is superior to 0.1Hz in the low-frequency range.

  7. Experiment about Drag Reduction of Bionic Non-smooth Surface in Low Speed Wind Tunnel

    Institute of Scientific and Technical Information of China (English)

    Tian Li-mei; Ren Lu-quan; Han Zhi-wu; Zhang Shi-cun

    2005-01-01

    The body surface of some organisms has non-smooth structure, which is related to drag reduction in moving fluid. To imitate these structures, models with a non-smooth surface were made. In order to find a relationship be tween drag reduction and the non-smooth surface, an orthogonal design test was employed in a low speed wind tunnel. Six factors likely to influence drag reduction were considered, and each factor tested at three levels. The six factors were the configuration, diameter/bottom width, height/depth, distribution, the arrangement of the rough structures on the experimental model and the wind speed. It was shown that the non-smooth surface causes drag reduction and the distribution of non-smooth structures on the model, and wind speed, are the predominant factors affecting drag reduction. Using analysis of variance, the optimal combination and levels were obtained, which were a wind speed of 44 m/s, distribution of the non-smooth structure on the tail of the experimental model, the configuration of riblets, diameter/bottom width of 1 mm, height/depth of 0.5 mm, arranged in a rhombic formation. At the optimal combination mentioned above, the 99% confidence interval for drag reduction was 11.13 % to 22.30%.

  8. Low Speed and High Speed Correlation of SMART Active Flap Rotor Loads

    Science.gov (United States)

    Kottapalli, Sesi B. R.

    2010-01-01

    Measured, open loop and closed loop data from the SMART rotor test in the NASA Ames 40- by 80- Foot Wind Tunnel are compared with CAMRAD II calculations. One open loop high-speed case and four closed loop cases are considered. The closed loop cases include three high-speed cases and one low-speed case. Two of these high-speed cases include a 2 deg flap deflection at 5P case and a test maximum-airspeed case. This study follows a recent, open loop correlation effort that used a simple correction factor for the airfoil pitching moment Mach number. Compared to the earlier effort, the current open loop study considers more fundamental corrections based on advancing blade aerodynamic conditions. The airfoil tables themselves have been studied. Selected modifications to the HH-06 section flap airfoil pitching moment table are implemented. For the closed loop condition, the effect of the flap actuator is modeled by increased flap hinge stiffness. Overall, the open loop correlation is reasonable, thus confirming the basic correctness of the current semi-empirical modifications; the closed loop correlation is also reasonable considering that the current flap model is a first generation model. Detailed correlation results are given in the paper.

  9. Economics of industrial cogeneration with a residual-oil-fired low-speed diesel

    Energy Technology Data Exchange (ETDEWEB)

    Santini, D.J.; Belak, F.J.; Bernard, M.J.; Stodolsky, F.; Suchy, K.W.

    1984-01-01

    The only residual-oil-fired low speed diesel cogeneration facility in the US has been in operation for a year at the Hoffman-LaRoche Vitamin C plant in Belvidere, NJ. Operating data for this grid-connected 23 MW facility are used to construct a generic evaluation of the economic desirability of such systems for industrial electric/thermal applications and industrial-thermal/commercial-electrical applications made possible by recent US legislation (PURPA). The post 1980 changes in relative electrical and residual oil prices are shown to have made oil fired on-site generation more attractive. The likely 1985-2005 movements of electricity and residual oil prices are discussed, along with risks of error in projections. The system is evaluated as a whole and on an incremental basis. Incremental analysis includes (1) the economics of steam and hot water use given the diesel and (2) the economics of system generation given industrial electric, steam and hot water loads. The sensitivity of the economics of the system to the full range of US electricity and residual oil prices is estimated. The effect of variation in system loads is examined. The economic desirability of the system is often great but is also highly variable geographically, largely as a function of local evaded electricity charges.

  10. Risk Factors Associated with Injury and Mortality from Paediatric Low Speed Vehicle Incidents: A Systematic Review

    Directory of Open Access Journals (Sweden)

    Anne Paul Anthikkat

    2013-01-01

    Full Text Available Objective. This study reviews modifiable risk factors associated with fatal and nonfatal injury from low-speed vehicle runover (LSVRO incidents involving children aged 0–15 years. Data Sources. Electronic searches for child pedestrian and driveway injuries from the peer-reviewed literature and transport-related websites from 1955 to 2012. Study Selection. 41 studies met the study inclusion criteria. Data Extraction. A systematic narrative summary was conducted that included study design, methodology, risk factors, and other study variables. Results. The most commonly reported risk factors for LSVRO incidents included age under 5 years, male gender, and reversing vehicles. The majority of reported incidents involved residential driveways, but several studies identified other traffic and nontraffic locations. Low socioeconomic status and rental accommodation were also associated with LSVRO injury. Vehicles were most commonly driven by a family member, predominantly a parent. Conclusion. There are a number of modifiable vehicular, environmental, and behavioural factors associated with LSVRO injuries in young children that have been identified in the literature to date. Strategies relating to vehicle design (devices for increased rearward visibility and crash avoidance systems, housing design (physical separation of driveway and play areas, and behaviour (driver behaviour, supervision of young children are discussed.

  11. Impact force of a low speed water droplet colliding on a solid surface

    Science.gov (United States)

    Li, Jingyin; Zhang, Bin; Guo, Penghua; Lv, Qian

    2014-12-01

    The impact forces of the low-speed water droplet colliding on a light and tiny aluminum plate were measured by using a highly sensitive piezoelectric force transducer. The one-degree freedom vibration model was employed to analyze the oscillation of the measured force signals, and the plate vibration was confirmed as the cause through elaborately designed experiments. The force data were obtained by using the low-pass Finite Impulse Response filter and was verified to be reliable. The effects of impact velocity and diameter of droplets on the impact force evolutions and peak forces were investigated. The results revealed that the impact process of a liquid droplet is quite different from that of a solid ball in the frequency spectrum and in the power function of the peak force. The droplet impact is closer to a plastic impact, while the other behaves more nearly an elastic impact. The influence of droplet size on erosion is dependent on the impact time duration, which increases with droplet diameter. On the other hand, the impact pressure is the main cause of the material erosion when impact velocity is taken as the influence factor.

  12. Comparison of Wind Power Converter Reliability with Low-Speed and Medium-Speed Permanent-Magnet Synchronous Generators

    DEFF Research Database (Denmark)

    Zhou, Dao; Blaabjerg, Frede; Franke, Toke

    2015-01-01

    of the low-speed (direct-drive) and medium-speed (one-stage) permanent-magnet synchronous generators are both promising solutions. This paper will assess and compare the reliability metrics for the machine-side converter for those two configurations. First, a translation from the mission profile......, according to the lifetime power cycles, the lifespan can be calculated when operating in various wind classes. It is concluded that, although the low-speed permanent-magnet synchronous generator is able to eliminate the gearbox, the lifespan of its machine-side converter is lower than the one-stage medium...

  13. Results of investigations on a 0.0405 scale model PRR version of the NR-SSV orbiter in the North American Aeronautical Laboratory low speed wind tunnel

    Science.gov (United States)

    Kingsland, R. B.; Vaughn, J. E.; Singellton, R.

    1973-01-01

    Experimental aerodynamic investigations were conducted in a low speed wind tunnel on a scale model space shuttle vehicle (SSV) orbiter. The purpose of the test was to investigate the longitudinal and lateral-directional aerodynamic characteristics of the space shuttle orbiter. Emphasis was placed on model component, wing-glove, and wing-body fairing effects, as well as elevon, aileron, and rudder control effectiveness. Angles of attack from - 5 deg to + 30 deg and angles of sideslip of - 5 deg, 0 deg, and + 5 deg were tested. Static pressures were recorded on base, fuselage, and wing surfaces. Tufts and talc-kerosene flow visualization techniques were also utilized. The aerodynamic force balance results are presented in plotted and tabular form.

  14. Low-Speed Fingerprint Image Capture System User`s Guide, June 1, 1993

    Energy Technology Data Exchange (ETDEWEB)

    Whitus, B.R.; Goddard, J.S.; Jatko, W.B.; Manges, W.W.; Treece, D.A.

    1993-06-01

    The Low-Speed Fingerprint Image Capture System (LS-FICS) uses a Sun workstation controlling a Lenzar ElectroOptics Opacity 1000 imaging system to digitize fingerprint card images to support the Federal Bureau of Investigation`s (FBI`s) Automated Fingerprint Identification System (AFIS) program. The system also supports the operations performed by the Oak Ridge National Laboratory- (ORNL-) developed Image Transmission Network (ITN) prototype card scanning system. The input to the system is a single FBI fingerprint card of the agreed-upon standard format and a user-specified identification number. The output is a file formatted to be compatible with the National Institute of Standards and Technology (NIST) draft standard for fingerprint data exchange dated June 10, 1992. These NIST compatible files contain the required print and text images. The LS-FICS is designed to provide the FBI with the capability of scanning fingerprint cards into a digital format. The FBI will replicate the system to generate a data base of test images. The Host Workstation contains the image data paths and the compression algorithm. A local area network interface, disk storage, and tape drive are used for the image storage and retrieval, and the Lenzar Opacity 1000 scanner is used to acquire the image. The scanner is capable of resolving 500 pixels/in. in both x and y directions. The print images are maintained in full 8-bit gray scale and compressed with an FBI-approved wavelet-based compression algorithm. The text fields are downsampled to 250 pixels/in. and 2-bit gray scale. The text images are then compressed using a lossless Huffman coding scheme. The text fields retrieved from the output files are easily interpreted when displayed on the screen. Detailed procedures are provided for system calibration and operation. Software tools are provided to verify proper system operation.

  15. Laboratory Scale Prototype of a Low-Speed Electrodynamic Levitation System Based on a Halbach Magnet Array

    Science.gov (United States)

    Iniguez, J.; Raposo, V.

    2009-01-01

    In this paper we analyse the behaviour of a small-scale model of a magnetic levitation system based on the Inductrack concept. Drag and lift forces acting on our prototype, moving above a continuous copper track, are studied analytically following a simple low-speed approach. The experimental results are in good agreement with the theoretical…

  16. Development of an efficient soymilk cream production method by papain digestion, heat treatment, and low-speed centrifugation.

    Science.gov (United States)

    Abe, Naoki; Wu, Chang-Yu; Kim, Yoon-Kyung; Fujii, Tomoyuki; Abe, Keietsu

    2015-01-01

    We developed the simple method of soymilk cream production from the high-fat soymilk, which was prepared by papain digestion and heat treatment. As a result of the treatment, high-fat soymilk was aggregated and it became possible to separate soymilk cream as the surface fraction by low-speed centrifugation (6000 × g, 10 min).

  17. Improvement of low speed induction generator performances and reducing the power of excitation and voltage control system

    Energy Technology Data Exchange (ETDEWEB)

    Budisan, N. [Politechnica Univ. of Timisoara (Romania); Hentea, T.; Mahil, S. [Purdue Univ. Calumet, Hammond, IN (United States); Madescu, G. [Romanian Academy, Timisoara (Romania)

    1996-12-31

    In this paper we present the results of our investigations concerning the utilization of induction generators at very low speed. It is shown that, by proper design, it is possible to obtain high efficiency and high power factor values. The optimized induction generators require lower reactive power resulting in lower size and price of the excitation control system. 4 refs., 2 figs.

  18. Nonlinear Time-Domain Strip Theory Formulation for Low-Speed Manoeuvering and Station-Keeping

    Directory of Open Access Journals (Sweden)

    Thor I. Fossen

    2004-10-01

    Full Text Available This paper presents a computer effective nonlinear time-domain strip theory formulation for dynamic positioning (DP and low-speed manoeuvring. Strip theory or 2D potential theory, where the ship is divided in 20 to 30 cross sections, can be used to compute the potential coefficients (added mass and potential damping and the exciting wave loads (Froude-Krylov and diffraction forces. Commercially available programs are ShipX (VERES by Marintek (Fathi, 2004 and SEAWAY by Amarcon (Journée & Adegeest, 2003, for instance. The proposed method can easily be extended to utilize other strip theory formulations or 3-D potential programs like WAMIT (2004. The frequency dependent potential damping, which in classic theory results in a convolution integral not suited for real-time simulation, is compactly represented by using the state-space formulation of Kristiansen & Egeland (2003. The separation of the vessel model into a low-frequency model (represented by zerofrequency added mass and damping and a wave-frequency model (represented by motion transfer functions or RAOs, which is commonly used for simulation, is hence made superfluous. Transformations of motions and coefficients between different coordinate systems and origins, i.e. data frame, hydrodynamic frame, body frame, inertial frame etc., are put into the rigid framework of Fossen (1994, 2002. The kinematic equations of motion are formulated in a compact nonlinear vector representation and the classical kinematic assumption that the Euler angles are small is removed. This is important for computation of accurate control forces at higher roll and pitch angles. The hydrodynamic forces in the steadily translating hydrodynamic reference frame (equilibrium axes are, however, assumed tobe linear. Recipes for computation of retardation functions are presented and frequency dependent viscous damping is included. Emphasis is placed on numerical computations and representation of the data from VERES and

  19. Large output-power, low-speed permanent magnet synchronous motor designs for ship propulsion drive

    Energy Technology Data Exchange (ETDEWEB)

    Rosu, M.

    2001-07-01

    Over the last decade, serious development has taken place in electric motor technology, and its impact is being felt in the shipbuilding community. This development has brought about a new generation of compact, high efficiency electrical machines. High performance, lightweight permanent magnet motors and generators have been developed for a wide range of applications including vehicle propulsion, power generation, pump and compressor drives. These machines combine the advances in magnetic materials and electronic design to provide shipbuilders new options for weight, energy and cost reduction. Permanent magnet machines were built in many different configurations and power classes, ranging from a few hundred watts to multi-megawatts for ship propulsion. Permanent magnet motors and generators for marine use were constructed and tested, all of these machines providing the same outstanding torque and power density. The basic electromagnetic, thermal and mechanical design approaches were established and tested in small prototype machines, the development of larger machines constituting the engineering later in the design process. The goal of this research work is to find an optimum solution in terms of design and suitability of a low-speed and high-power permanent magnet motor for ship propulsion drive. In this work, the study-case analyses are limited to the electromagnetic part of the motor. Two types of radial flux permanent magnet synchronous motors are designed and optimised to meet the propulsion requirements. The first motor has the permanent magnets mounted on the surface of the rotor while the second motor has the permanent magnets mounted on the rotor surface and covered by laminated pole shoes. In their construction, high-energy NdFeB permanent magnets were chosen. These magnetic materials provide a sufficient airgap magnetic flux density with a low volume of material. Moreover, the NdFeB permanent magnets are endowed with high coercivity. As an immediate

  20. Overview of Low-Speed Aerodynamic Tests on a 5.75% Scale Blended-Wing-Body Twin Jet Configuration

    Science.gov (United States)

    Vicroy, Dan D.; Dickey, Eric; Princen, Norman; Beyar, Michael D.

    2016-01-01

    The NASA Environmentally Responsible Aviation (ERA) Project sponsored a series of computational and experimental investigations of the propulsion and airframe integration issues associated with Hybrid-Wing-Body (HWB) or Blended-Wing-Body (BWB) configurations. NASA collaborated with Boeing Research and Technology (BR&T) to conduct this research on a new twin-engine Boeing BWB transport configuration. The experimental investigations involved a series of wind tunnel tests with a 5.75-percent scale model conducted in two low-speed wind tunnels. This testing focused on the basic aerodynamics of the configuration and selection of the leading edge Krueger slat position for takeoff and landing. This paper reviews the results and analysis of these low-speed wind tunnel tests.

  1. Statistical predictions for the dynamics of a low-speed system: Newtonian versus special-relativistic mechanics.

    Directory of Open Access Journals (Sweden)

    Shiuan-Ni Liang

    Full Text Available The newtonian and special-relativistic statistical predictions for the mean, standard deviation and probability density function of the position and momentum are compared for the periodically-delta-kicked particle at low speed. Contrary to expectation, we find that the statistical predictions, which are calculated from the same parameters and initial gaussian ensemble of trajectories, do not always agree if the initial ensemble is sufficiently well-localized in phase space. Moreover, the breakdown of agreement is very fast if the trajectories in the ensemble are chaotic, but very slow if the trajectories in the ensemble are non-chaotic. The breakdown of agreement implies that special-relativistic mechanics must be used, instead of the standard practice of using newtonian mechanics, to correctly calculate the statistical predictions for the dynamics of a low-speed system.

  2. Statistical predictions for the dynamics of a low-speed system: Newtonian versus special-relativistic mechanics.

    Science.gov (United States)

    Liang, Shiuan-Ni; Lan, Boon Leong

    2012-01-01

    The newtonian and special-relativistic statistical predictions for the mean, standard deviation and probability density function of the position and momentum are compared for the periodically-delta-kicked particle at low speed. Contrary to expectation, we find that the statistical predictions, which are calculated from the same parameters and initial gaussian ensemble of trajectories, do not always agree if the initial ensemble is sufficiently well-localized in phase space. Moreover, the breakdown of agreement is very fast if the trajectories in the ensemble are chaotic, but very slow if the trajectories in the ensemble are non-chaotic. The breakdown of agreement implies that special-relativistic mechanics must be used, instead of the standard practice of using newtonian mechanics, to correctly calculate the statistical predictions for the dynamics of a low-speed system.

  3. Low-Speed Control of Heavy-Load Transfer Robot with Long Telescopic Boom Based on Stribeck Friction Model

    Directory of Open Access Journals (Sweden)

    Bo You

    2012-01-01

    Full Text Available The severe low-speed creep phenomenon occurs in the telescopic boom system of a heavy-load transfer robot with a long telescopic boom as a result of nonlinear friction. In order to improve control precision and operation performance at low speeds, we built a three-loop control nonlinear model of an AC servo motor with Stribeck friction disturbance. Traditional proportional-integral-derivative controller (PID and fuzzy PID controls were, respectively, adopted in the position loop, and the control performance was simulated. The results showed that a system with fuzzy PID control eliminates “flat top” position tracking and “dead zone” speed tracking, which are generated by traditional PID, and thereby decreases the effect of friction on the performance of the servo system. This elimination also improved the tracking accuracy and robustness of the system.

  4. Performance of a Low Speed Axial Compressor Rotor Blade Row under Different Inlet Distortions

    Directory of Open Access Journals (Sweden)

    R. Taghavi Zenouz

    2017-05-01

    Full Text Available Responses of an axial compressor isolated rotor blade row to various inlet distortions have been investigated utilizing computational fluid dynamic technique. Distortions have been imposed by five screens of different geometries, but with the same blockage ratio. These screens were embedded upstream of the rotor blade row. Flow fields are simulated in detail for compressor design point and near stall conditions. Performance curves for distorted cases are extracted and compared to the undisturbed case. Flow simulations and consequent performance characteristics show that the worst cases belong to non-symmetric blockages, i.e., those of partial circumferential configurations. These cases produce the largest wakes which can disturb the flow, considerably. Superior performances correspond to the inner and outer continuous circumferential distortion screens. Since, they produce no significant disturbances to the main flow in comparison to the non-symmetric screens.

  5. Experimental Research for Refractories Used in High-Turbulent-Mixer (HTM)-Reactor

    Institute of Scientific and Technical Information of China (English)

    2001-01-01

    The high turbulent mixer (HTM) process is benefit for improving the quality of iron and steel, but the refractory of the reactor is easy to be eroded by slag and liquid metal at high temperature. Especially for the violent mixing in HTM, refractory can also be impacted by molten metal (iron or steel), so it is very important to study and find out new refractory to meet the demand of HTM. Suitable refractory not only can stand the eroding of slag and liquid metal, but also can reduce the loss of electromagnetic energy. According to the experimental results, the influence of different refractory on electromagnetic force is unconspicuous, the refractory with Al2O3-base is better than that with MgO-base for standing the erosion by slag and iron. Al2O3-base refractory is more suitable for HTM process.

  6. Highly Turbulent Counterflow Flames: A Laboratory Scale Benchmark for Practical Combustion Systems

    Science.gov (United States)

    Gomez, Alessandro

    2013-11-01

    Since the pioneering work of Weinberg's group at Imperial College in the `60s, the counterflow system has been the workhorse of laminar flame studies. Recent developments have shown that it is also a promising benchmark for highly turbulent (Ret ~ 1000) nonpremixed and premixed flames of direct relevance to gasturbine combustion. Case studies will demonstrate the versatility of the system in mimicking real flame effects, such as heat loss and flame stratification in premixed flames, and the compactness of the combustion region. The system may offer significant advantages from a computational viewpoint, including: a) aerodynamic flame stabilization near the interface between the two opposed jets, with ensuing simplifications in the prescription of boundary conditions; b) a fiftyfold reduction of the domain of interest as compared to conventional nonpremixed jet flames at the same Reynolds number; and c) millisecond mean residence times, which is particularly useful for DNS/LES computational modeling, and for soot suppression in the combustion of practical fuels.

  7. Mathematical Modeling,Field Calibration and Numerical Simulation of Low-Speed Mixed Traffic Flow in Cities

    Institute of Scientific and Technical Information of China (English)

    1998-01-01

    Withtherapiddevelopmentoftransportationandautomobileindustry,theconflictbetweenmotormanufactureandhighwayconstructionbecomess...

  8. M2-F1 in flight during low-speed car tow

    Science.gov (United States)

    1963-01-01

    The M2-F1 shown in flight during a low-speed car tow runs across the lakebed. Such tests allowed about two minutes to test the vehicle's handling in flight. NASA Flight Research Center (later redesignated the Dryden Flight Research Center) personnel conducted as many as 8 to 14 ground-tow flights in a single day either to test the vehicle in preparation for air tows or to train pilots to fly the vehicle before they undertook air tows. The wingless, lifting body aircraft design was initially concieved as a means of landing an aircraft horizontally after atmospheric reentry. The absence of wings would make the extreme heat of re-entry less damaging to the vehicle. In 1962, Dryden management approved a program to build a lightweight, unpowered lifting body as a prototype to flight test the wingless concept. It would look like a 'flying bathtub,' and was designated the M2-F1, the 'M' referring to 'manned' and 'F' referring to 'flight' version. It featured a plywood shell placed over a tubular steel frame crafted at Dryden. Construction was completed in 1963. The first flight tests of the M2-F1 were over Rogers Dry Lake at the end of a tow rope attached to a hopped-up Pontiac convertible driven at speeds up to about 120 mph. This vehicle needed to be able to tow the M2-F1 on the Rogers Dry Lakebed adjacent to NASA's Flight Research Center (FRC) at a minimum speed of 100 miles per hour. To do that, it had to handle the 400-pound pull of the M2-F1. Walter 'Whitey' Whiteside, who was a retired Air Force maintenance officer working in the FRC's Flight Operations Division, was a dirt-bike rider and hot-rodder. Together with Boyden 'Bud' Bearce in the Procurement and Supply Branch of the FRC, Whitey acquired a Pontiac Catalina convertible with the largest engine available. He took the car to Bill Straup's renowned hot-rod shop near Long Beach for modification. With a special gearbox and racing slicks, the Pontiac could tow the 1,000-pound M2-F1 110 miles per hour in 30

  9. Investigations on Low Speed Axial Compressor with Forward and Backward Sweep

    Institute of Scientific and Technical Information of China (English)

    M.Govardhan; O.G.Krishna Kumar; N.Sitaram

    2007-01-01

    In the recent past, experimental studies have shown some advantages of blade lean and sweep in axial compressors. As most of the experimental results are combined with other features, it is difficult to determine the effect of individual parameters on the performance of the compressor. The present numerical studies are aimed at understanding the performance and three-dimensional flow pattern at the exit of swept and unswept rotors. Three rotors, namely; unswept, 200 forward swept and 200 backward swept rotors are analysed with a specific intention of understanding the pattern of the blade boundary layer flow. The analysis was done using a fully three-dimensional viscous CFD code CFX-5. Results indicated reduction in pressure rise with sweep. Backward sweep is detrimental as far as the performance near endwalls is considered. On the other hand total pressure loss in the wake in mid span region is less with backward sweep, which favours its application here. However, backward sweep adversely affects the stall margin. The ability of the forward sweep to deflect the streamlines towards hub gets diminished at low flow rates. Forward sweep changes the streamline pattern in such a way that the suction surface streamlines are deflected towards the hub and the pressure surface streamlines are deflected towards the casing. An opposite behaviour is observed in backward swept rotors.

  10. Suppression of broadband noise radiated by a low-speed fan in a duct.

    Science.gov (United States)

    Huang, L; Ma, X; Feng, L G

    2010-07-01

    Attenuation of ducted fan noise remains a technical challenge in the low frequency range as traditional duct lining becomes ineffective. This study proposes a reactive method to suppress the sound radiation from an axial-flow fan. The method is particularly effective in the low frequency region and covers a broad band. Its effect is derived from two mechanisms. One is the reduction in the confining effects of duct walls when the duct radius is increased; the other is the acoustic interference between the direct radiation from the fan and reflections by the duct junctions. This interference is always destructive for axial dipoles when the frequency approaches zero. This performance differs from normal passive control methods, which become totally ineffective toward zero frequency. An approximate plane-wave theory explains the essential physics of the method, and its quantitative prediction is found to agree well with a full numerical simulation using a spectral method of Chebyshev collocation. The latter is validated by experiment using an axial-flow fan in a duct of finite length. Broadband noise reduction is achieved while the flow speed is kept unchanged. Practical difficulties of implementation for a fan with high pressure increase are discussed.

  11. Remote operation over low speed, high latency links; Operacao remota confiavel usando circuitos de baixa velocidade e alta latencia

    Energy Technology Data Exchange (ETDEWEB)

    Nunes, Marcelo D.; Nunes, Ildemar P. [Transportadora Brasileira Gasoduto Bolivia Brasil S.A., Rio de Janeiro, RJ (Brazil)

    2004-07-01

    Remote Control and monitoring of a compressor station with more than 3000 tags can be a hard task to accomplish over a low speed satellite link. This paper presents Datasync, an application specially developed to provide acceptable performance levels over a VSAT link. One of its main features is to enable the establishment of communication dead bands. The dead bands can be altered while the application is running (no restart is needed), so that the operator is able to increase a specific tag's dead band immediately after detecting that it is reporting too many exceptions, which would cause an increase on the traffic and response times. (author)

  12. Impact of PLL Parameters Variation on the Pulsating Voltage Injection Technique Based PMSM Position Estimation at Low Speeds

    Directory of Open Access Journals (Sweden)

    Olfa Bel Hadj Brahim Kechiche

    2014-06-01

    Full Text Available This study highlights the impact of an universal Phase Locked Loop (PLL parameters variation on PMSM position estimation at low speeds. Indeed, the PLL parameters variation impact on the PMSM rotor position estimation performance and robustness cannot be neglected anymore. For this purpose, the study presents the theory and simulation results of a demodulation scheme applied to Sensorless PMSM control based on the Pulsating Voltage Injection (PVI technique. Comprehensive simulations, carried out under MATLAB/SIMULINK®, are discussed according to the variation of the PLL proportional and integral parameters.

  13. Error Reduction in Portable, Low-Speed Weigh-In-Motion (Sub-0.1 Percent Error)

    Energy Technology Data Exchange (ETDEWEB)

    Abercrombie, Robert K [ORNL; Hively, Lee M [ORNL; Scudiere, Matthew B [ORNL; Sheldon, Frederick T [ORNL

    2008-01-01

    We present breakthrough findings based on significant modifications to the Weigh-in-Motion (WIM) Gen II approach, so-called the modified Gen II. The revisions enable slow speed weight measurements at least as precise as in ground static scales, which are certified to 0.1% error. Concomitant software and hardware revisions reflect a philosophical and practical change that enables an order of magnitude improvement in low-speed weighing precision. This error reduction breakthrough is presented within the context of the complete host of commercial and governmental application rationale including the flexibility to extend information and communication technology for future needs.

  14. New gravity-capillary waves at low speeds. Part 2: Nonlinear geometries

    CERN Document Server

    Trinh, Philippe H

    2015-01-01

    When traditional linearised theory is used to study gravity-capillary waves produced by flow past an obstruction, the geometry of the object is assumed to be small in one or several of its dimensions. In order to preserve the nonlinear nature of the obstruction, asymptotic expansions in the low-Froude or low-Bond number limits can be derived, but here, the solutions are waveless to every order. This is because the waves are in fact, exponentially small, and thus beyond-all-orders of regular asymptotics; their formation is a consequence of the divergence of the asymptotic series and the associated Stokes Phenomenon. In Part 1, we showed how exponential asymptotics could be used to study the problem when the size of the obstruction is first linearised. In this paper, we extend the analysis to the nonlinear problem, thus allowing the full geometry to be considered at leading order. When applied to the classic problem of flow over a step, our analysis reveals the existence of six classes of gravity-capillary wave...

  15. Acute duodenal Crohn's disease successfully managed with low-speed elemental diet infusion via nasogastric tube: A case report

    Institute of Scientific and Technical Information of China (English)

    Takayuki Yamamoto; Maki Nakahigashi; Satoru Umegae; Tatsushi Kitagawa; Koichi Matsumoto

    2006-01-01

    Duodenal Crohn's disease is rare, and patients without obstruction are treated medically. We herein report one case whose duodenal Crohn's disease was successfully managed with low-speed elemental diet infusion through a nasogastric tube. A 28-year-old female developed acute duodenal Crohn's disease. Upper GI radiologic and endoscopic examinations showed a stricture in the duodenal bulb. Using the duodenal biopsy specimens,mucosal cytokine levels were measured; interleukin (IL)-1β, IL-6, IL-8, and tumor necrosis factor-α levels were remarkably elevated. For initial 2 wk, powdered mesalazine was orally given but it was not effective. For the next 2 wk, she was treated with low-speed elemental diet therapy using a commercially available ElentalTM,which was infused continuously through a nasogastric tube using an infusion pump. The tip of the nasogastric tube was placed at an immediate oral side of the pylorus.The infusion speed was 10 mL/h (usual speed, 100 mL/h).After the 2-wk treatment, her symptoms were very much improved, and endoscopically, the duodenal stricture and inflammation improved. The duodenal mucosal cytokine levels remarkably decreased compared with those before the treatment. Although our experience was limited, lowspeed elemental diet infusion through a nasogastric tube may be a useful treatment for acute duodenal Crohn's disease.

  16. Low-speed Impact Simulations into Regolith in Support of Asteroid Sampling Mechanism Design I.: Comparison with 1-g Experiments

    CERN Document Server

    Schwartz, Stephen R; Richardson, Derek C; Yano, Hajime

    2014-01-01

    This study is carried out in the framework of sample-return missions to asteroids that use a low-speed projectile as the primary component of its sampling mechanism (e.g., JAXA's Hayabusa and Hayabusa2 missions). We perform numerical simulations of such impacts into granular materials using different projectile shapes under Earth's gravity. We then compare the amounts of ejected mass obtained in our simulations against what was found in experiments that used similar setups, which allows us to validate our numerical approach. For the targets, we consider 2 different monodisperse grain-diameter sizes: 5 mm and 3 mm. The impact speed of the projectile is 11 m s$^{-1}$ directed downward, perpendicular to the surface of the targets. Using an implementation of the soft-sphere discrete element method (SSDEM) in the $N$-Body gravity tree code PKDGRAV, previously validated in the context of low-speed impacts into sintered glass bead agglomerates, we find a noticeable dependence of the amount of ejected mass on the pro...

  17. Coronal Heating and Acceleration of the High/Low-Speed Solar Wind by Fast/Slow MHD Shock Trains

    CERN Document Server

    Suzuki, T K

    2004-01-01

    We investigate coronal heating and acceleration of the high- and low-speed solar wind in the open field region by dissipation of fast and slow magnetohydrodynamical (MHD) waves through MHD shocks. Linearly polarized \\Alfven (fast MHD) waves and acoustic (slow MHD) waves travelling upwardly along with a magnetic field line eventually form fast switch-on shock trains and hydrodynamical shock trains (N-waves) respectively to heat and accelerate the plasma. We determine one dimensional structure of the corona from the bottom of the transition region (TR) to 1AU under the steady-state condition by solving evolutionary equations for the shock amplitudes simultaneously with the momentum and proton/electron energy equations. Our model reproduces the overall trend of the high-speed wind from the polar holes and the low-speed wind from the mid- to low-latitude streamer except the observed hot corona in the streamer. The heating from the slow waves is effective in the low corona to increase the density there, and plays ...

  18. Performance Investigation of Low-Speed Electric Vehicles%低速电动汽车的性能研究

    Institute of Scientific and Technical Information of China (English)

    吴正斌; 胡坚耀; 李程宇

    2015-01-01

    电动汽车是解决能源危机和环境污染的有效方法,但就目前情况来看,电动汽车大规模使用仍需时日。尽管如此,低速电动汽车目前已在中国低端电动汽车市场取得了成功。文章探讨了低速电动汽车的行驶特性、动态性能、电池性能和能量效率。通过底盘测功机实验测试与室外道路实验,分析了低速电动汽车的负载特性和过载特性,研究不同电池对低速电动车性价比的影响。虽然目前锂离子电池比铅酸电池成本更高,但实际应用中,锂离子电池效率更高、全寿命行驶距离更长。直流驱动电机有优秀的过载能力,但电机系统的低效率限制了低速电动汽车的整车能量效率。因此,开发低成本、高效率的电池及电机驱动系统是提高低速电动车性价比的有效途径。%Electric vehicle is an effective solution to the fossil fuel energy resource crisis and environmental pollution, but there is a wide gap between current market conditions and the anticipated products. However, low-speed electric vehicles have been commercially successful in the low-end performance electric vehicle market in China. In this paper, the ride characteristics, dynamic performance, battery performance, and power efficiency of a low-speed electric vehicle were examined. The vehicle characteristics were measured through dynamometer and road tests. The overload performance was also tested under the drive power more than 4 times the rated value. The effects of different batteries on the cost performance of low-speed electric vehicles were also analysed. Although the lithium-ion polymer battery is currently more costly than the lead-acid battery, the increased efifciency of this battery provides a more economical full-cycle lifetime driving distance for practical applications. The low power efifciency of the DC drive motor and its control system limit the general power efifciency of the low-speed

  19. The Strikingly Uniform, Highly Turbulent Interstellar Medium of the Most Luminous Galaxy in the Universe

    CERN Document Server

    Diaz-Santos, T; Blain, A W; Tsai, C -W; Aravena, M; Eisenhardt, P; Wu, J; Stern, D; Bridge, C

    2015-01-01

    Observed at z = 4.601 and with L_bol = 3.5 x 10^14 Lsun, W2246-0526 is the most luminous galaxy known in the Universe, and hosts a deeply-buried active galactic nucleus (AGN)/super-massive black hole (SMBH). Discovered using the Wide-field Infrared Survey Explorer (WISE), W2246-0526 is classified as a Hot Dust Obscured Galaxy (Hot DOG), based on its luminosity and dust temperature. Here we present spatially resolved ALMA [CII]157.7um observations of W2246-0526, providing unique insight into the kinematics of its interstellar medium (ISM). The measured [CII]-to-far-infrared ratio is ~2 x 10^-4, implying ISM conditions that compare only with the most obscured, compact starbursts and AGN in the local Universe today. The spatially resolved [CII] line is strikingly uniform and very broad, 500-600 km/s wide, extending throughout the entire galaxy over about 2.5 kpc, with modest shear. Such a large, homogeneous velocity dispersion indicates a highly turbulent medium. W2246-0526 is unstable in terms of the energy and...

  20. 低速磁悬浮列车牵引计算算法研究%Traction Calculation Algorithm Research for Low-speed Maglev Train

    Institute of Scientific and Technical Information of China (English)

    饶攀; 刘少克

    2012-01-01

    Based on a traction calculation model for low-speed maglev train, a new strategy of traction calculation was put forward. According to the strategy, key technology and flow charts of the algorithms were presented. Simulation software was formulated, by which the Beijing S1 route was calculated. With proposed algorithms, high speed and low consumption of the train were achieved.%为完成低速磁悬浮列车牵引计算,建立了低速磁悬浮列车牵引计算模型,提出了一种新的牵引策略,阐述了该策略的关键技术和算法流程的设计,编制了牵引计算仿真软件,并对北京S1线进行了牵引计算.采用该算法控制列车达到了列车运行速度快、节能降耗的目的.

  1. Applying low-speed modeling method to high pressure turbine stage%低速模拟技术在高压涡轮级中的应用

    Institute of Scientific and Technical Information of China (English)

    魏巍; 马宏伟

    2013-01-01

    借鉴低速模拟技术在航空发动机高压压气机研究中的成功经验,探索了将其应用于高压涡轮部件时的气动设计方法,提出了一种改进的叶型重设计方法.以此方法为设计准则,选取E3发动机高压涡轮的第1级为原型高压涡轮,设计了与其相似的低速涡轮试验设备.在设计过程中保证了两者之间相等或相近的稠度、展弦比等结构参数,相近的效率、负荷系数、沿径向分布的效率和气流角等气动参数,以及类似的无量纲叶片表面等熵马赫数分布形式.数值模拟结果表明:由于低速涡轮设备的落压比、总温比等参数均与原型高压涡轮差别较大,压气机低速模拟中常用的流量系数、叶片表面压力分布等相似参数不再适用.按照给出的结构和气动相似参数所设计的低速涡轮模型达到设计要求,其能够反映出原型高压涡轮主要的气动参数变化趋势,能够作为涡轮内部气动热力学研究的试验载体.%Based on the successful experience of applying low-speed modeling technology to high pressure compressor of aero-engine, the aerodynamic design method of turbine with similar technology was investigated, and an improved blade redesign method was illustrated.Referring to an adjusted similarity principle, a low-speed turbine research facility was established, which was aerodynamically and thermally represented by the first stage of prototype high pressure turbine of E3 core.In the design process, identical structural parameters between the prototype and the expected facility, such as solidity, span-to-chord ratio, and tip clearance-to-span ratio, were assured while similar aerodynamic performance was verified; besides, acceptable similarity of non-dimensional blade surface isentropic Mach number distribution was ascertained.Numerical simulation results shows that flow coefficient and blade surface pressure distribution are not suitable in the modeling of turbine for the

  2. A cost-effective 100-Gb/s transmitter with low-speed optoelectronic devices and high spectral efficiency

    Institute of Scientific and Technical Information of China (English)

    Junming Gao; Qingjiang Chang; Tao Wang; Yikai Su

    2008-01-01

    A 100-Gb/s high-speed optical transmitter is proposed and experimentally demonstrated. Based on frequency-quadrupling technique, two sub-channels with a fixed 50-GHz spacing are obtained from one laser source. Using return-to-zero differential quadrature phase-shift keying (RZ-DQPSK) modulation format and polarization multiplexing (PolMux), only low-speed electronic devices of 12.5 GHz are needed for the 100-Gb/s transmitter. This eliminates the need of ultrahigh-speed optoelectronic devices and thus greatly reduces the cost. The experimental results show that this transmitter can achieve good performance in dispersion tolerance of a 25-km single mode fiber (SMF).

  3. A simulation study of the low-speed characteristics of a light twin with an engine-out

    Science.gov (United States)

    Stewart, E. C.; Moul, T. M.; Brown, P. W.

    1983-01-01

    Potential safety advantages provided by the two engines on a light twin aircraft are not realized in practice as evidenced by recent engine-failure accident statistics. These statistics showed twice the fatality rate from engine failure for twins as for single-engine aircraft. The statistics showed also that one-half of the fatal engine-out accidents involved a stall. An improvement of the low-speed engine-out characteristics is, therefore, needed. An investigation of the engine-out characteristics of light twin-engine aircraft is currently being conducted as part of the comprehensive stall/spin program for general aviation aircraft. The present study is concerned with the first phase of this program. The primary objective of this study is to advance the understanding of the basic flight dynamics and piloting problems for an engine-out condition. An all-digital computer system was used in the conducted simulation study.

  4. Fractional-Order Generalized Predictive Control: Application for Low-Speed Control of Gasoline-Propelled Cars

    Directory of Open Access Journals (Sweden)

    M. Romero

    2013-01-01

    Full Text Available There is an increasing interest in using fractional calculus applied to control theory generalizing classical control strategies as the PID controller and developing new ones with the intention of taking advantage of characteristics supplied by this mathematical tool for the controller definition. In this work, the fractional generalization of the successful and spread control strategy known as model predictive control is applied to drive autonomously a gasoline-propelled vehicle at low speeds. The vehicle is a Citroën C3 Pluriel that was modified to act over the throttle and brake pedals. Its highly nonlinear dynamics are an excellent test bed for applying beneficial characteristics of fractional predictive formulation to compensate unmodeled dynamics and external disturbances.

  5. Integrated Condition Monitoring and Prognosis Method for Incipient Defect Detection and Remaining Life Prediction of Low Speed Slew Bearings

    Directory of Open Access Journals (Sweden)

    Wahyu Caesarendra

    2017-04-01

    Full Text Available This paper presents an application of multivariate state estimation technique (MSET, sequential probability ratio test (SPRT and kernel regression for low speed slew bearing condition monitoring and prognosis. The method is applied in two steps. Step (1 is the detection of the incipient slew bearing defect. In this step, combined MSET and SPRT is used with circular-domain kurtosis, time-domain kurtosis, wavelet decomposition (WD kurtosis, empirical mode decomposition (EMD kurtosis and the largest Lyapunov exponent (LLE feature. Step (2 is the prediction of the selected features’ trends and the estimation of the remaining useful life (RUL of the slew bearing. In this step, kernel regression is used with time-domain kurtosis, WD kurtosis and the LLE feature. The application of the method is demonstrated with laboratory slew bearing acceleration data.

  6. Is Low Speed Electric Vehicle a Disruptive Innovation?%低速电动汽车是破坏性创新吗

    Institute of Scientific and Technical Information of China (English)

    张长令; 王丽萍

    2013-01-01

    Low speed electric vehicle is a special economic phenomenon in China Low speed electric vehicle develops rapidly since 2005. Currently, the development of low speed electric vehicle industry in China has entered the key stage of industrialization. Because of the characteristics of disruptive product, low speed electric vehicle is usually attributed to disruptive innovation pointing to traditional automobile. Based on disruptive innovation theory, connecting with current situation of low speed electric vehicle industry in China, this paper analyzes the challenges on disruptive innovation theory brought by low speed electric vehicle industry. The analysis indicated that low speed electric vehicle is not a disruptive product to traditional automobile.%低速电动汽车是中国特有的经济现象.中国低速电动汽车产业自2005年以来开始快速发展,目前已进入产业化的关键阶段.由于具有破坏性产品的特点,低速电动汽车往往被归结为针对传统汽车的破坏性创新.本文在破坏性创新理论的基础上,结合低速中国电动汽车产业发展的特点,深入分析了低速电动汽车产业发展对破坏性创新理论带来的挑战.分析表明,低速电动汽车并非传统汽车的破坏性产品.

  7. Full-scale S-76 rotor performance and loads at low speeds in the NASA Ames 80- by 120-Foot Wind Tunnel. Vol. 1

    Science.gov (United States)

    Shinoda, Patrick M.

    1996-01-01

    A full-scale helicopter rotor test was conducted in the NASA Ames 80- by 120-Foot Wind Tunnel with a four-bladed S-76 rotor system. Rotor performance and loads data were obtained over a wide range of rotor shaft angles-of-attack and thrust conditions at tunnel speeds ranging from 0 to 100 kt. The primary objectives of this test were (1) to acquire forward flight rotor performance and loads data for comparison with analytical results; (2) to acquire S-76 forward flight rotor performance data in the 80- by 120-Foot Wind Tunnel to compare with existing full-scale 40- by 80-Foot Wind Tunnel test data that were acquired in 1977; (3) to evaluate the acoustic capability of the 80- by 120- Foot Wind Tunnel for acquiring blade vortex interaction (BVI) noise in the low speed range and compare BVI noise with in-flight test data; and (4) to evaluate the capability of the 80- by 120-Foot Wind Tunnel test section as a hover facility. The secondary objectives were (1) to evaluate rotor inflow and wake effects (variations in tunnel speed, shaft angle, and thrust condition) on wind tunnel test section wall and floor pressures; (2) to establish the criteria for the definition of flow breakdown (condition where wall corrections are no longer valid) for this size rotor and wind tunnel cross-sectional area; and (3) to evaluate the wide-field shadowgraph technique for visualizing full-scale rotor wakes. This data base of rotor performance and loads can be used for analytical and experimental comparison studies for full-scale, four-bladed, fully articulated rotor systems. Rotor performance and structural loads data are presented in this report.

  8. Pretest Report for the Full Span Propulsive Wing/Canard Model Test in the NASA Langley 4 x 7 Meter Low Speed Wind Tunnel Second Series Test

    Science.gov (United States)

    Stewart, V. R.

    1986-01-01

    A full span propulsive wing/canard model is to be tested in the NASA Langley Research Center (LaRC) 4 x 7 meter low speed wind tunnel. These tests are a continuation of the tests conducted in Feb. 1984, NASA test No.290, and are being conducted under NASA Contract NAS1-17171. The purpose of these tests is to obtain extensive lateral-directional data with a revised fuselage concept. The wings, canards, and vertical tail of this second test series model are the same as tested in the previous test period. The fuselage and internal flow path have been modified to better reflect an external configuration suitable for a fighter airplane. Internal ducting and structure were changed as required to provide test efficiency and blowing control. The model fuselage tested during the 1984 tests was fabricated with flat sides to provide multiple wing and canard placement variations. The locations of the wing and canard are important variables in configuration development. With the establishment of the desired relative placement of the lifting surfaces, a typically shaped fuselage has been fabricated for these tests. This report provides the information necessary for the second series tests of the propulsive wing/canard model. The discussion in this report is limited to that affected by the model changes and to the second series test program. The pretest report information for test 290 which is valid for the second series test was published in Rockwell report NR 83H-79. This report is presented as Appendix 1 and the modified fuselage stress report is presented as Appendix 2 to this pretest report.

  9. Low-speed impact simulations into regolith in support of asteroid sampling mechanism design I: Comparison with 1-g experiments

    Science.gov (United States)

    Schwartz, Stephen R.; Michel, Patrick; Richardson, Derek C.; Yano, Hajime

    2014-11-01

    This study is carried out in the framework of sample-return missions to asteroids that use a low-speed projectile as the primary component of its sampling mechanism (e.g., JAXA's Hayabusa and Hayabusa2 missions). We perform numerical simulations of such impacts into granular materials using different projectile shapes under Earth's gravity. We then compare the amounts of ejected mass obtained in our simulations against what was found in experiments that used similar setups, which allows us to validate our numerical approach. We then investigate the sensitivity of various parameters involved in the contacts between grains on the amount of mass that is ejected. For the targets, we consider 2 different monodisperse grain-diameter sizes: 5 mm and 3 mm. The impact speed of the projectile is 11 m s-1, and is directed downward, perpendicular to the surface of the targets. Using an implementation of the soft-sphere discrete element method (SSDEM) in the N-body gravity tree code pkdgrav, previously validated in the context of low-speed impacts into sintered glass bead agglomerates, we find a noticeable dependence of the amount of ejected mass on the projectile shape. As found in experiments, in the case of the larger target grain size (5 mm), a conically shaped projectile ejects a greater amount of mass than do projectiles of other shapes, including disks and spheres. We then find that numerically the results are sensitive to the normal coefficient of restitution of the grains, especially for impacts into targets comprising smaller grains (3 mm). We also find that static friction plays a more important role for impacts into targets comprising the larger grains. As a preliminary demonstration, one of these considered setups is simulated in a microgravity environment. As expected, a reduction in gravity increases both the amount of ejected mass and the timescale of the impact process. A dedicated quantitative study in microgravity is the subject of future work. We also plan

  10. Analytical and Numerical Deflection Study on the Structure of 10 kW Low Speed Permanent Magnet Generator

    Directory of Open Access Journals (Sweden)

    Hilman Syaeful Alam

    2012-12-01

    Full Text Available Analytical and numerical studies of the deflection in the structure of 10 kW low speed permanent magnet generator (PMG have been discussed in this paper. This study is intended to prevent failure of the structure when the prototype is made. Numerical analysis was performed with the finite-element method (FEM. Flux density, weight and temperature of the components are the required input parameters. Deflection observed were the movements of the two main rotor components, namely the rim and shaft, where the maximum deflection allowed at the air gap between rotor and stator should be between 10% to 20% of the air gap clearance or 0.1000 mm to 0.2000 mm. Base on the analysis, total deflection of the analytic calculation was 0.0553 mm, and numerical simulation was 0.0314 mm. Both values were in the acceptable level because it was still below the maximum allowed deflection. These results indicate that the structure of a permanent magnet generator (rim and shaft can be used safely.

  11. Modeling spatial trajectories in dynamics testing using basis splines: application to tracking human volunteers in low-speed frontal impacts.

    Science.gov (United States)

    Samuels, Marina A; Reed, Matthew P; Arbogast, Kristy B; Seacrist, Thomas

    2016-01-01

    Designing motor vehicle safety systems requires knowledge of whole body kinematics during dynamic loading for occupants of varying size and age, often obtained from sled tests with postmortem human subjects and human volunteers. Recently, we reported pediatric and adult responses in low-speed (<4 g) automotive-like impacts, noting reductions in maximum excursion with increasing age. Since the time-based trajectory shape is also relevant for restraint design, this study quantified the time-series trajectories using basis splines and developed a statistical model for predicting trajectories as a function of body dimension or age. Previously collected trajectories of the head, spine, and pelvis were modeled using cubic basis splines with eight control points. A principal component analysis was conducted on the control points and related to erect seated height using a linear regression model. The resulting statistical model quantified how trajectories became shorter and flatter with increasing body size, corresponding to the validation data-set. Trajectories were then predicted for erect seated heights corresponding to pediatric and adult anthropomorphic test devices (ATDs), thus generating performance criteria for the ATDs based on human response. This statistical model can be used to predict trajectories for a subject of specified anthropometry and utilized in subject-specific computational models of occupant response.

  12. Analysis of a Split-Plot Experimental Design Applied to a Low-Speed Wind Tunnel Investigation

    Science.gov (United States)

    Erickson, Gary E.

    2013-01-01

    A procedure to analyze a split-plot experimental design featuring two input factors, two levels of randomization, and two error structures in a low-speed wind tunnel investigation of a small-scale model of a fighter airplane configuration is described in this report. Standard commercially-available statistical software was used to analyze the test results obtained in a randomization-restricted environment often encountered in wind tunnel testing. The input factors were differential horizontal stabilizer incidence and the angle of attack. The response variables were the aerodynamic coefficients of lift, drag, and pitching moment. Using split-plot terminology, the whole plot, or difficult-to-change, factor was the differential horizontal stabilizer incidence, and the subplot, or easy-to-change, factor was the angle of attack. The whole plot and subplot factors were both tested at three levels. Degrees of freedom for the whole plot error were provided by replication in the form of three blocks, or replicates, which were intended to simulate three consecutive days of wind tunnel facility operation. The analysis was conducted in three stages, which yielded the estimated mean squares, multiple regression function coefficients, and corresponding tests of significance for all individual terms at the whole plot and subplot levels for the three aerodynamic response variables. The estimated regression functions included main effects and two-factor interaction for the lift coefficient, main effects, two-factor interaction, and quadratic effects for the drag coefficient, and only main effects for the pitching moment coefficient.

  13. Low speed maneuvering flight of the rose-breasted cockatoo (Eolophus roseicapillus). II. Inertial and aerodynamic reorientation.

    Science.gov (United States)

    Hedrick, T L; Usherwood, J R; Biewener, A A

    2007-06-01

    The reconfigurable, flapping wings of birds allow for both inertial and aerodynamic modes of reorientation. We found evidence that both these modes play important roles in the low speed turning flight of the rose-breasted cockatoo Eolophus roseicapillus. Using three-dimensional kinematics recorded from six cockatoos making a 90 degrees turn in a flight corridor, we developed predictions of inertial and aerodynamic reorientation from estimates of wing moments of inertia and flapping arcs, and a blade-element aerodynamic model. The blade-element model successfully predicted weight support (predicted was 88+/-17% of observed, N=6) and centripetal force (predicted was 79+/-29% of observed, N=6) for the maneuvering cockatoos and provided a reasonable estimate of mechanical power. The estimated torque from the model was a significant predictor of roll acceleration (r(2)=0.55, Pflight dynamics (approximately -0.45), were required to bring our estimates of reorientation due to aerodynamic torque back into conjunction with the measured changes in orientation. Our estimates of inertial reorientation were statistically significant predictors of the measured reorientation within wingbeats (r(2) from 0.2 to 0.37, Pflight muscles: the pectoralis, supracoracoideus, biceps brachii and extensor metacarpi radialis (r(2) from 0.27 to 0.45, Pflight maneuvers rely on production of asymmetries throughout the flight apparatus rather than in a specific set of control or turning muscles.

  14. Impact coefficient and reliability of mid-span continuous beam bridge under action of extra heavy vehicle with low speed

    Institute of Scientific and Technical Information of China (English)

    刘波; 王有志; 胡朋; 袁泉

    2015-01-01

    To analyze the dynamic response and reliability of a continuous beam bridge under the action of an extra heavy vehicle, a vehicle–bridge coupled vibration model was established based on the virtual work principle and vehicle–bridge displacement compatibility equation, which can accurately simulate the dynamic characteristics of the vehicle and bridge. Results show that deck roughness has an important function in the effect of the vehicle on the bridge. When an extra heavy vehicle passes through the continuous beam bridge at a low speed of 5 km/h, the impact coefficient reaches a high value, which should not be disregarded in bridge safety assessments. Considering that no specific law exists between the impact coefficient and vehicle speed, vehicle speed should not be unduly limited and deck roughness repairing should be paid considerable attention. Deck roughness has a significant influence on the reliability index, which decreases as deck roughness increases. For the continuous beam bridge in this work, the reliability index of each control section is greater than the minimum reliability index. No reinforcement measures are required for over-sized transport.

  15. Test Data Report, Low-Speed Wind Tunnel Drag Test of a 2/5 Scale Lockheed AH-56 Cheyenne Door-Hinge Hub

    Science.gov (United States)

    2016-07-01

    SPECIAL REPORT RDMR-AD-16-03 TEST DATA REPORT, LOW-SPEED WIND TUNNEL DRAG TEST OF A 2/5 SCALE LOCKHEED AH-56 CHEYENNE DOOR-HINGE HUB Robert D...TYPE AND DATES COVERED Final 4. TITLE AND SUBTITLE Test Data Report, Low-Speed Wind Tunnel Drag Test of a 2/5 Scale Lockheed AH-56 Cheyenne...Research, Development and Engineering Center (AMRDEC) conducted a drag test of a non-rotating 2/5 scale Lockheed AH-56 Cheyenne main rotor hub in

  16. Prediction, postdiction, and perceptual length contraction: a Bayesian low-speed prior captures the cutaneous rabbit and related illusions

    Directory of Open Access Journals (Sweden)

    Daniel eGoldreich

    2013-05-01

    Full Text Available Illusions provide a window into the brain’s perceptual strategies. In certain illusions, an ostensibly task-irrelevant variable influences perception. For example, in touch as in audition and vision, the perceived distance between successive punctate stimuli reflects not only the actual distance but curiously the inter-stimulus time. Stimuli presented at different positions in rapid succession are drawn perceptually towards one another. This effect manifests in several illusions, among them the startling cutaneous rabbit, in which taps delivered to as few as two skin positions appear to hop progressively from one position to the next, landing in the process on intervening areas that were never stimulated. Here we provide an accessible step-by-step exposition of a Bayesian perceptual model that replicates the rabbit and related illusions. The Bayesian observer optimally joins uncertain estimates of spatial location with the expectation that stimuli tend to move slowly. We speculate that this expectation – a Bayesian prior – represents the statistics of naturally occurring stimuli, learned by humans through sensory experience. In its simplest form, the model contains a single free parameter, tau: a time constant for space perception. We show that the Bayesian observer incorporates both pre- and post-dictive inference. Directed spatial attention affects the prediction-postdiction balance, shifting the model’s percept towards the attended location, as observed experimentally in humans. Applying the model to the perception of multi-tap sequences, we show that the low-speed prior fits perception better than an alternative, low-acceleration prior. We discuss the applicability of our model to related tactile, visual, and auditory illusions. To facilitate future model-driven experimental studies, we present a convenient freeware computer program that implements the Bayesian observer; we invite investigators to use this program to create their own

  17. Riding performance on a conventional bicycle and a pedelec in low speed exercises : objective and subjective evaluation of middle-aged and older persons.

    NARCIS (Netherlands)

    Kovácsová, M. Winter, J.C.F. de Schwab, A.L. Christoph, M. Twisk, D.A.M. & Hagenzieker, M.P.

    2016-01-01

    This study investigated cycling performance of middle-aged (30–45 years old; n = 30) versus older (65+ years; n = 31) participants during low-speed tasks for which stabilization skills are known to be important. Additionally, participants’ self-ratings of their cycling skills and performance were as

  18. 78 FR 16358 - Safety Advisory 2013-02; Low-Speed, Wheel-Climb Derailments of Passenger Equipment With “Stiff...

    Science.gov (United States)

    2013-03-14

    ... the full range of component tolerances (e.g., spring heights) and maintenance limits (e.g., wheel wear... determined. Additionally, FRA understands that softer springs, which may be selected to provide better wheel... Federal Railroad Administration Safety Advisory 2013-02; Low-Speed, Wheel-Climb Derailments of...

  19. 低速增升装置失速特性预测研究%Prediction Research on Stall Characteristic for Low-speed High-lift System

    Institute of Scientific and Technical Information of China (English)

    成水燕; 李中武; 聂智军; 梁益华

    2014-01-01

    民机低速增升装置失速特性是具有挑战性的空气动力学难题之一,决定着飞机起、降阶段机翼处于流动分离或尾迹干扰状态时的操纵稳定性,是气动设计必须关注的重要方面。利用基于N-S方程的自研多块结构网格计算软件和混合网格计算软件,对NASA高升力梯形机翼标准模型开展了失速特性计算研究,系统评估了计算软件、计算网格、湍流模型等主要因素对失速特性的影响,获得了有效预测高升力构型失速特性的计算方案,并将其成功应用于工程实际,为增升装置失速特性计算评估提供了有意义的参考。%Stall characteristic of civil aircraft low-speed high-lift device is one of the challenging aerody-namics problems .It determines the control stability of wing in the flow separation or wake interference state when airplane is taking off and landing .It is an important aspect that aerodynamic design must be paying attention to .In this paper ,CFD computational study is performed on the standard model of NASA high-lift trapezoidal wing by using our in-house multi-block structured mesh solver and unstructured mesh solver based on RANS equation .Predictive capabilities for stall characteristic from solvers ,meshes and turbulence models are systematically evaluated .Calculation scheme which can effectively predict stall characteristic of high-lift configurations is obtained and it was applied in practical engineering successful-ly .The aim is to provide a meaningful guideline for stall characteristic prediction of civil aircraft high-lift system .

  20. 中低速磁悬浮列车控制及网络系统%Medium-low Speed Maglev Train Control and Network System

    Institute of Scientific and Technical Information of China (English)

    粟爱军; 袁文烨; 许义景; 李一叶; 何文惠

    2012-01-01

    介绍了中低速磁悬浮列车控制及网络系统的设计思路与系统组成,从网络控制系统总线、拓扑、功能等角度对网络控制系统进行了阐述,通过车辆逻辑控制模块、列车线的分析,对中低速磁悬浮列车硬线继电控制系统进行了说明.%Design and configuration of network control system for medium-low speed maglev train were presented. Network control system was described from system bus, topology, and functions, etc. With analysis of logical vehicle control module and train line, medium-low speed maglev train hard-wire relay control system was indicated.

  1. TY5KM型接触网作业车低速走行系统%Low Speed Running System of Type TY5KM Catenary Work Vehicle

    Institute of Scientific and Technical Information of China (English)

    臧坤

    2015-01-01

    This paper mainly introduces the main structure, the technical parameters and the main characteristic of the low-speed system of the model TY5KM catenary working car. On the basic of the original power transmission system, the model TY5KM catenary wording car increase a line construction work the low-speed system, the walking speed can stepless speed regulation in 0~10 km/h, implemented the two-way low–speed running, it also on the operation platform and the driv-er’s cab control the low-speed system manipulation. The low-speed system can switch with the main power transmission, adopt pneumatic control oil pump, the motor clutch and when a failure hand control on-off control.%介绍了TY5KM型接触网作业车低速走行系统的主要结构、主要技术参数及主要特点。 TY5KM接触网作业车在原有动力传动系统的基础上加设一套施工作业低速走行系统。走行速度在0~10 km/h范围内无级调速,实现了作业车双向的低速走行,亦可实现在作业车平台上及司机室内控制低速走行操纵。低速走行与主动力传动能够可靠的切换,采用气动操纵油泵、马达离合及故障时手动操纵控制离合。

  2. Differences in glance behavior between drivers using a rearview camera, parking sensor system, both technologies, or no technology during low-speed parking maneuvers.

    Science.gov (United States)

    Kidd, David G; McCartt, Anne T

    2016-02-01

    This study characterized the use of various fields of view during low-speed parking maneuvers by drivers with a rearview camera, a sensor system, a camera and sensor system combined, or neither technology. Participants performed four different low-speed parking maneuvers five times. Glances to different fields of view the second time through the four maneuvers were coded along with the glance locations at the onset of the audible warning from the sensor system and immediately after the warning for participants in the sensor and camera-plus-sensor conditions. Overall, the results suggest that information from cameras and/or sensor systems is used in place of mirrors and shoulder glances. Participants with a camera, sensor system, or both technologies looked over their shoulders significantly less than participants without technology. Participants with cameras (camera and camera-plus-sensor conditions) used their mirrors significantly less compared with participants without cameras (no-technology and sensor conditions). Participants in the camera-plus-sensor condition looked at the center console/camera display for a smaller percentage of the time during the low-speed maneuvers than participants in the camera condition and glanced more frequently to the center console/camera display immediately after the warning from the sensor system compared with the frequency of glances to this location at warning onset. Although this increase was not statistically significant, the pattern suggests that participants in the camera-plus-sensor condition may have used the warning as a cue to look at the camera display. The observed differences in glance behavior between study groups were illustrated by relating it to the visibility of a 12-15-month-old child-size object. These findings provide evidence that drivers adapt their glance behavior during low-speed parking maneuvers following extended use of rearview cameras and parking sensors, and suggest that other technologies which

  3. Grid-Free LES 3D Vortex Method for the Simulation of Tubulent Flows Over Advanced Lifting Surfaces Project

    Data.gov (United States)

    National Aeronautics and Space Administration — Turbulent flows associated with advanced aerodynamic designs represent a considerable challenge for accurate prediction. For example, the flow past low-speed wings...

  4. Evaluation of the hybrid III and Q-series pediatric ATD upper neck loads as compared to pediatric volunteers in low-speed frontal crashes.

    Science.gov (United States)

    Seacrist, Thomas; Mathews, Emily A; Balasubramanian, Sriram; Maltese, Matthew R; Arbogast, Kristy B

    2013-11-01

    Debate exists in the automotive community regarding the validity of the pediatric ATD neck response and corresponding neck loads. Previous research has shown that the pediatric ATDs exhibit hyper-flexion and chin-to-chest contact resulting in overestimations of neck loads and neck injury criteria. Our previous work comparing the kinematics of the Hybrid III and Q-series 6 and 10-year-old ATDs to pediatric volunteers in low-speed frontal sled tests revealed decreased ATD cervical and thoracic spine excursions. These kinematic differences may contribute to the overestimation of upper neck loads by the ATD. The current study compared upper neck loads of the Hybrid III and Q-series 6 and 10-year-old ATDs against size-matched male pediatric volunteers in low-speed frontal sled tests. A 3-D near-infrared target tracking system quantified the position of markers on the ATD and pediatric volunteers (head top, nasion, bilateral external auditory meatus). Shear force (F x ), axial force (F z ), bending moment (M y ), and head angular acceleration ([Formula: see text]) were calculated about the upper neck using standard equations of motion. In general, the ATDs underestimated axial force and overestimated bending moment compared to the human volunteers. The Hybrid III 6, Q6, and Q10 exhibited reduced head angular acceleration and modest increases in upper neck shear compared to the pediatric volunteers. The reduction in axial force and bending moment has important implications for neck injury predictions as both are used when calculating N ij . These analyses provide insight into the biofidelity of the pediatric ATD upper neck loads in low-speed crash environments.

  5. 中低速磁浮道岔组装测量技术研究%Measurement Technology Research on Assembling of Middle-low Speed Maglev Turnout

    Institute of Scientific and Technical Information of China (English)

    郑莹

    2016-01-01

    Combined with the assembly measurement for the domestic first middle-low maglev transit operation line and the measurement requirements of high precision dimension and shape in the middle-low speed maglev turnout,this paper put forward the methods of basic measuring and positioning,turnout beam measurement positioning and F rail measurement po-sitioning.The operation results showed that the use of instrument measuring tools such as high precision total station instru-ment,straightedge and steel wire string,successfully completed the assembling and measuring of middle-low speed maglev turnout,and could meet the measurement requirements of high precision dimension and shape in the middle-low speed ma-glev turnout.%结合国内首条中低速磁浮交通运营线道岔的组装测量以及中低速磁浮道岔高精度尺寸和形位的测量要求,提出了中低速磁浮道岔基础测量定位、道岔梁测量定位及 F 轨测量定位测量方法,运用结果表明利用高精度全站仪及直尺、钢丝弦线等仪器量具,成功完成了中低速磁浮道岔的组装测量,满足了中低速磁浮道岔高精度尺寸和形位的测量要求。

  6. 大型低风速风电场运行分析%An Analysis of Large Low-speed Wind Farm Operation

    Institute of Scientific and Technical Information of China (English)

    张小雷; 高崇伦; 吴爱国

    2013-01-01

      近年来,风能资源丰富的区域受到资源和规模等因素的限制,人们悄然把目光转向更为广阔的低风速区域。安徽来安低风速风电场是全国首个低风速风电场。本文介绍了来安风电场的基本情况,从海拔高度对发电量的影响、森林(粗糙度)对发电量的影响、风切变和湍流强度对功率曲线的影响等四个方面分析风电场的运行情况,总结了低风速风电场运行的特点和部分规律,为以后风电场建设提供参考。%In recent years, the development of wind areas with rich wind resource gradually is limited by the resources and the scale of wind farm. People turned to explore broad low-speed wind area.The low-speed wind farm of Lai'an is the frst one in China.The paper introduced the main situation of the Lai'an wind farm. According to comparison of the impact of altitude and forest(roughness) for power generation, the impact of wind shear and turbulence intensity for the power curve, this paper analyzed the operating conditions of the wind farm and summed up the characteristics and regularities of low-speed wind farm operation. It aims to provide reference for the future construction of the wind farm.

  7. Pulsed Doppler Radar for Low Speed Target Detection%脉冲多普勒雷达低速目标检测技术

    Institute of Scientific and Technical Information of China (English)

    郭玲红; 李亚立

    2012-01-01

    The principles of pulsed doppler radar for target detection and the characteristics of low speed target detection are analysed. The leakages of emission signal, local oscillator signal, frequency multiply signal of synchronizing pulse and crystal oscillator output are the reasons that effecting of pulsed doppler radar on the low speed target detection. So isolation' s raising, wideband signal reception and emission signal frequency offset are the solution measures to realize low speed target detection effectively. Experimental study proved the validity of analysis and measures.%通过对脉冲多普勒雷达目标检测原理和低速目标检测特点的分析,确定了来自于雷达系统中的发射信号泄露、本振信号泄露、同步脉冲及DDS信号倍频分量泄露、晶振信号倍频分量泄露等是影响脉冲多普勒雷达对于低速目标检测的主要因素,依托现有硬件水平,通过提高系统的收发隔离度、采用宽带接收和发射频率预偏移等技术措施,保证泄漏信号远小于回波信号,从而有效地实现了对低速目标的检测,并通过实验验证了设计的正确性和措施的有效性。

  8. Flutter parametric studies of cantilevered twin-engine-transport type wing with and without winglet. Volume 1: Low-speed investigations

    Science.gov (United States)

    Bhatia, K. G.; Nagaraja, K. S.

    1984-01-01

    Flutter characteristics of a cantilevered high aspect ratio wing with winglet were investigated. The configuration represented a current technology, twin-engine airplane. A low-speed and high-speed model were used to evaluate compressibility effects through transonic Mach numbers and a wide range of mass-density ratios. Four flutter mechanisms were obtained in test, as well as analysis from various combinations of configuration parameters. The coupling between wing tip vertical and chordwise motions was shown to have significant effect under some conditions. It is concluded that for the flutter model configurations studied, the winglet related flutter was amenable to the conventional flutter analysis techniques.

  9. Evaluating the Acoustic Effect of Over-the-Rotor Foam-Metal Liner Installed on a Low Speed Fan Using Virtual Rotating Microphone Imaging

    Science.gov (United States)

    Sutliff, Daniel L.; Dougherty, Robert P.; Walker, Bruce E.

    2010-01-01

    An in-duct beamforming technique for imaging rotating broadband fan sources has been used to evaluate the acoustic characteristics of a Foam-Metal Liner installed over-the-rotor of a low-speed fan. The NASA Glenn Research Center s Advanced Noise Control Fan was used as a test bed. A duct wall-mounted phased array consisting of several rings of microphones was employed. The data are mathematically resampled in the fan rotating reference frame and subsequently used in a conventional beamforming technique. The steering vectors for the beamforming technique are derived from annular duct modes, so that effects of reflections from the duct walls are reduced.

  10. Summary of information on low-speed lateral-directional derivatives due to rate of change of sideslip beta prime

    Science.gov (United States)

    Coe, P. L., Jr.; Graham, A. B.; Chambers, J. R.

    1975-01-01

    The results presented show that the magnitudes of the aerodynamic stability derivatives due to rate of change of sideslip become quite large at high angles of attack for swept- and delta-wing configurations, and that such derivatives have large effects on the calculated dynamic stability of these configurations at high angles of attack. The wind-tunnel test techniques used to measure the beta prime derivatives and various approaches used to predict them are discussed. Both the conventional oscillating-airfoil theory and the lag-of-the-sidewash theory are shown to be inadequate for predicting the vertical-tail contribution to the acceleration-in-sideslip derivative; a flow-field-lag theory, which is discussed, appears to give qualitative agreement with experimental data for a current twin-jet fighter configuration.

  11. Performance evaluation of the general characteristics based off-lattice Boltzmann and DUGKS methods for low speed continuum flows: A comparative study

    CERN Document Server

    Zhu, Lianhua; Guo, Zhaoli

    2015-01-01

    The general characteristics based off-lattice Boltzmann scheme (BKG) proposed by Bardow et~al.(2006), and the discrete unified gas kinetic scheme (DUGKS) are two methods that successfully overcome the time step restriction by the collision time, which is commonly seen in many other kinetic schemes. Basically, the BKG scheme is a time splitting scheme, while the DUGKS is an un-split finite volume scheme. In this work, we first perform a theoretical analysis of the two schemes in the finite volume framework by comparing their numerical flux evaluations. It is found that the effects of collision term are considered in the reconstructions of the cell-interface distribution function in both schemes, which explains why they can overcome the time step restriction and can give accurate results even as the time step is much larger than the collision time. The difference between the two schemes lies in the treatment of the integral of the collision term, in which the Bardow's scheme uses the rectangular rule while the ...

  12. The effects of low-speed swimming following exhaustive exercise on metabolic recovery and swimming performance in brook trout (Salvelinus fontinalis).

    Science.gov (United States)

    Kieffer, James D; Kassie, Roshini S; Taylor, Susan G

    2011-01-01

    Experiments were conducted to determine whether low-speed swimming during recovery from exhaustive exercise improved both metabolic recovery and performance during a swimming challenge. For these experiments, brook trout were allowed to recover from exhaustive exercise for 2 h while swimming at 0, 0.5, 1.0, or 1.5 body length (BL) s(-1) or allowed to recover from exhaustive exercise for 1, 2, or 3 h while swimming at 1.0 BL s(-1). At the appropriate interval, either (i) muscle and blood samples were removed from the fish or (ii) fish were assessed for performance (i.e., fatigue time) during a fixed-interval swimming test. Low-speed swimming during recovery from exhaustive exercise resulted in significantly longer fatigue times compared with fish recovering in still water (i.e., 0 BL s(-1)). However, swimming during recovery did not expedite recovery of muscle lactate or blood variables (e.g., lactate, osmolarity, glucose). These observations suggest that metabolic recovery and subsequent swimming performance may not be directly linked and that other factors play a role in swimming recovery in brook trout.

  13. Injection barrel with a tapered structure for a low speed and small size cryogenic hydrogen pellet in medium-sized plasma fusion devices

    Science.gov (United States)

    Motojima, G.; Sakamoto, R.; Okada, H.; Nagasaki, K.; Yamada, H.; Nakamura, Y.; Kado, S.; Kobayashi, S.; Konoshima, S.; Minami, T.; Ohshima, S.; Yamamoto, S.; Mizuuchi, T.; Mutoh, T.

    2016-10-01

    An injection barrel was designed and fabricated for a small size 0.8 mm cryogenic pellet with a low speed of 200-300 m/s in medium-sized plasma fusion devices. Pellet injection with pneumatic acceleration was examined using a conventional in situ technique. A tapered structure was applied in the downstream side of the injection barrel to satisfy the requirement of pellet speed reduction by expansion of the propellant gas. Shadowgraph and light gate measurements show that the intact pellets have speeds of 260 ± 30 m/s and a typical size of 1.1-1.2 mm. The pellet ablation code based on a neutral gas shielding model shows that the penetration depth of the measured pellet parameters does not cross the plasma center, even in medium-sized plasma devices such as the Heliotron J helical device. The injection barrel with a tapered structure developed in this study is feasible for low speed pellet injection.

  14. Design of Suspension Power Supply for Mid-Low Speed Maglev Train%中低速磁浮列车悬浮电源的设计

    Institute of Scientific and Technical Information of China (English)

    魏培华; 黄芳军; 孙立辉; 唐海燕; 刘长清

    2012-01-01

    A DC/DC converter is used in suspension power supply for mid-low speed maglev train, which can provide DC 330 V power for suspension controller and charge DC 330 V battery. It's one of the key equipments of mid-low speed maglev train for normal operating. Its main circuit topology, basic control method and current sharing technology are presented, and the structural design and engineering applications are also introduced.%中低速磁浮列车的悬浮电源采用DC/DC变换器,主要为悬浮控制器提供DC330V电源和为DC330V蓄电池充电,是中低速磁浮列车正常运行的关键部件之一。文章主要介绍了中低速磁浮列车悬浮电源主电路拓扑结构、基本控制方法、均流控制等关键技术,并介绍了其结构设计及应用。

  15. 微海流能量收集及自动释放装置%Harvesting Energy of Low Speed Sea Currents and Auto Releasing Device

    Institute of Scientific and Technical Information of China (English)

    冀功祥; 邓小青; 田应元

    2014-01-01

    This essay focuses on the introduction of energy harvesting and storage of low speed sea currents and auto-releas-ing device. The assembly of the device mainly consists of impeller,gear reduction unit, mechanical energe storage device and auto releasing device. The project has been proved to be reliable, efficient and can be used in deep sea. With futher modifi-cation, it can even be used to harvest energy of low speed wind.%介绍一种微海流能量收集及自动释放装置,该装置主要由叶轮、减速机构、机械蓄能机构和自动释放机构4个部分组成。通过试验验证,该装置工作可靠、效率高,可用于深海。经过改进,还可用于微风能收集。

  16. Injection barrel with a tapered structure for a low speed and small size cryogenic hydrogen pellet in medium-sized plasma fusion devices.

    Science.gov (United States)

    Motojima, G; Sakamoto, R; Okada, H; Nagasaki, K; Yamada, H; Nakamura, Y; Kado, S; Kobayashi, S; Konoshima, S; Minami, T; Ohshima, S; Yamamoto, S; Mizuuchi, T; Mutoh, T

    2016-10-01

    An injection barrel was designed and fabricated for a small size 0.8 mm cryogenic pellet with a low speed of 200-300 m/s in medium-sized plasma fusion devices. Pellet injection with pneumatic acceleration was examined using a conventional in situ technique. A tapered structure was applied in the downstream side of the injection barrel to satisfy the requirement of pellet speed reduction by expansion of the propellant gas. Shadowgraph and light gate measurements show that the intact pellets have speeds of 260 ± 30 m/s and a typical size of 1.1-1.2 mm. The pellet ablation code based on a neutral gas shielding model shows that the penetration depth of the measured pellet parameters does not cross the plasma center, even in medium-sized plasma devices such as the Heliotron J helical device. The injection barrel with a tapered structure developed in this study is feasible for low speed pellet injection.

  17. LNGCME-GI低速机与TFDE电力推进对比%Comparative Analysis of LNGC ME-GI Low-speed Engine and TFDE Electric Propulsion

    Institute of Scientific and Technical Information of China (English)

    杨波

    2016-01-01

    In order to satisfy the economy and environmental protection requirements of the ship , large LNG carrier propul-sion system was improved .In view of the target ship , from a technical point the two latest propulsion ways of the ME-GI low-speed engine propulsion and TFDE electric propulsion were analyzed emphatically .The analytical results showed that the ME-GI low-speed engine to promote both economic and environmental protection systems are better than the current mainstream TFDE e -lectric propulsion system , it will gradually become the mainstream of future large LNG carrier form .%针对满足船舶的经济性和环保性要求,大型LNG运输船推进系统更新换代的问题,从技术角度着重对比目标船型ME-GI低速机推进与TFDE电力推进2种最新的推进方式。结果可见,ME-GI低速机推进系统不论是经济性还是环保性都优于目前主流的TFDE电力推进系统,将成为未来大型LNG运输船的主流推进形式。

  18. A comparative study of Cr-X-N (X=Zr, Si) coatings for the improvement of the low-speed torque efficiency of a hydraulic piston pump

    Science.gov (United States)

    Hong, Yeh-Sun; Lee, Sang-Yul

    2008-02-01

    The internal parts of hydraulic pumps operating at variable speed should be protected from insufficient lubrication. The axial piston type pumps employ a steel-base cylinder barrel rotating on a soft bronze valves plate with a slide contact, where the insufficient lubrication of these components can cause rapid wear of the valve plate and increase the friction loss. In this study, the cylinder barrel surface was deposited with CrZrN coatings, which were expected to improve the tribological contact with a valve plate under low-speed mixed lubrication conditions. Its effect on the improvement of the low-speed torque efficiency of a hydraulic piston pump was investigated and compared with that from the CrSiN coating. The coated cylinder barrels showed much lower friction coefficients and wear rates of the valve plates than the uncoated plasma-nitride one. In particular, the CrZrN coatings revealed better performance than the CrSiN coatings. By representing the improvement in the torque efficiency of the whole pump based upon the degree of the friction coefficient reduction, the CrZrN coatings exhibited approximately a 0.35% higher improvement at 300 bar and 100 rpm than CrSiN coatings. The possible failure modes of the coatings coated on the barrel were sugested and the microstructures of the coatings seemed to have a strong effect on the film failure mode.

  19. Low-speed aerodynamic performance of an aspect-ratio-10 supercritical-wing transport model equipped with a full-span slat and part-span and full-span double-slotted flaps

    Science.gov (United States)

    Morgan, H. L., Jr.

    1981-01-01

    An investigation was conducted in the Langley 4 by 7 Meter Tunnel to determine the static longitudinal and lateral directional aerodynamic characteristics of an advanced aspect ratio 10 supercritical wing transport model equipped with a full span leading edge slat as well as part span and full span trailing edge flaps. This wide body transport model was also equipped with spoiler and aileron roll control surfaces, flow through nacelles, landing gear, and movable horizontal tails. Six basic wing configurations were tested: (1) cruise (slats and flaps nested), (2) climb (slats deflected and flaps nested), (3) part span flap, (4) full span flap, (5) full span flap with low speed ailerons, and (6) full span flap with high speed ailerons. Each of the four flapped wing configurations was tested with leading edge slat and trailing edge flaps deflected to settings representative of both take off and landing conditions. Tests were conducted at free stream conditions corresponding to Reynolds number of 0.97 to 1.63 x 10 to the 6th power and corresponding Mach numbers of 0.12 to 0.20, through an angle of attack range of 4 to 24, and a sideslip angle range of -10 deg to 5 deg. The part and full span wing configurations were also tested in ground proximity.

  20. Forest Ecosystem respiration estimated from eddy covariance and chamber measurements under high turbulence and substantial tree mortality from bark beetles

    Science.gov (United States)

    Speckman, Heather N.; Frank, John M.; Bradford, John B.; Miles, Brianna L.; Massman, William J.; Parton, William J.; Ryan, Michael G.

    2015-01-01

    Eddy covariance nighttime fluxes are uncertain due to potential measurement biases. Many studies report eddy covariance nighttime flux lower than flux from extrapolated chamber measurements, despite corrections for low turbulence. We compared eddy covariance and chamber estimates of ecosystem respiration at the GLEES Ameriflux site over seven growing seasons under high turbulence (summer night mean friction velocity (u*) = 0.7 m s−1), during which bark beetles killed or infested 85% of the aboveground respiring biomass. Chamber-based estimates of ecosystem respiration during the growth season, developed from foliage, wood and soil CO2 efflux measurements, declined 35% after 85% of the forest basal area had been killed or impaired by bark beetles (from 7.1 ±0.22 μmol m−2 s−1 in 2005 to 4.6 ±0.16 μmol m−2 s−1 in 2011). Soil efflux remained at ~3.3 μmol m−2 s−1 throughout the mortality, while the loss of live wood and foliage and their respiration drove the decline of the chamber estimate. Eddy covariance estimates of fluxes at night remained constant over the same period, ~3.0 μmol m−2 s−1 for both 2005 (intact forest) and 2011 (85% basal area killed or impaired). Eddy covariance fluxes were lower than chamber estimates of ecosystem respiration (60% lower in 2005, and 32% in 2011), but the mean night estimates from the two techniques were correlated within a year (r2 from 0.18-0.60). The difference between the two techniques was not the result of inadequate turbulence, because the results were robust to a u* filter of > 0.7 m s−1. The decline in the average seasonal difference between the two techniques was strongly correlated with overstory leaf area (r2=0.92). The discrepancy between methods of respiration estimation should be resolved to have confidence in ecosystem carbon flux estimates.

  1. Design and analysis of full pitch winding and concentrated stator pole winding three-phase flux reversal machine for low speed application

    Indian Academy of Sciences (India)

    D S More; Hari Kalluru; B G Fernandes

    2008-10-01

    The flux reversal machine (FRM) is a doubly-salient stator permanent magnet machine with flux linkage reversal in the stator concentrated winding. The existing machines at low speed, low power (2·4 kW, 300 rpm) range are not economical. FRM topology is best suited for this application. An attempt has been made to improve the power density of machine by introducing full pitch winding. Full pitch winding FRM (FPFRM) has higher power density than the conventional concentrated stator pole winding FRM (CSPFRM). Design and comparative analysis of FPFRM and CSPFRM are made. Both machines are designed for 88·58 Nm and 300 rpm. Design details of both machines are presented. Finite Element Method (FEM) analysis is carried out to evaluate and compare the performance of CSPFRM and FPFRM. Series capacitive compensation is provided for better voltage regulation of both machines.

  2. Interior assembly process for Changsha Medium and low speed maglev train%长沙中低速磁浮列车内饰组装工艺

    Institute of Scientific and Technical Information of China (English)

    姚永虎

    2016-01-01

    阐述了长沙中低速磁浮列车的部分内饰结构、组装工艺,分析了内饰组装过程中的工艺难点、预防措施以及解决方案,并通过制定内饰质量控制标准实现了内饰组装的一致性和美观性。%This paper analyses the interior structure and assembly process of medium and low speed maglev train of Changsha.It presents the aporia of interior assembly,and carries out the standard of quality controlling to enforce the consistency and artistry of interior assembly.

  3. Low-Speed Yawed-Rolling Characteristics of a Pair of 56-Inch-Diameter, 32-Ply-Rating, Type 7 Aircraft Tires

    Science.gov (United States)

    Thompson, Wilbur E.; Horne, Walter B.

    1959-01-01

    The low-speed (up to 4 miles per hour) yawed-rolling characteristics of two 56 x 16 32-ply-rating, type 7 aircraft tires under straight-yawed rolling were determined over a range of inflation pressures and yaw angles for a vertical load approximately equal to 75 percent of the rated vertical load. The quantities measured or determined included cornering force, drag force self-alining torque, pneumatic caster vertical tire deflection, yaw angle, and relaxation length. During straight-yawed rolling the normal force generally increased with increasing yaw angle within the test range. The self-alining torque increased to a maximum value and then decreased with increasing angle of yaw. The pneumatic caster tended to decrease with increasing yaw angle.

  4. OBLIQUE TOWING TEST AND MANEUVER SIMULATION AT LOW SPEED AND LARGE DRIFT ANGLE FOR DEEP SEA OPEN-FRAMED REMOTELY OPERATED VEHICLE

    Institute of Scientific and Technical Information of China (English)

    FAN Shi-bo; LIAN Lian; REN Ping; HUANG Guo-liang

    2012-01-01

    This article presents the newly designed oblique towing test in the horizontal plane for the scaled model of 4 500 m deep sea open-framed Remotely Operated Vehicle (ROV),which is being researched and developed by Shanghai Jiao Toug University.Accurate hydrodynamics coefficients measurement is significant for the maneuverability and control system design.The scaled model of ROV was constructed by 1∶1.6.Hydrodynamics tests of large drift angle were conducted through Large Amplitude Horizontal Planar Motion Mechanism (LAHPMM) under low speed.Multiple regression method is adopted to process the test data and obtain the related hydrodynamic coefficients.Simulations were designed for the horizontal plane motion of large drift angle to verify the coefficients calculated.And the results show that the data can satisfy with the design requirements of the ROV developed.

  5. 中低速磁浮技术引领绿色交通%Medium and Low-speed Maglev Leads to Green Transport

    Institute of Scientific and Technical Information of China (English)

    简炼

    2011-01-01

    The basic principles and characteristics of medium-and low-speed magnetic levitated system as a new type of rail system are described in the paper with the applied scope proposed. Through its application research in Shenzhen metrt Line 8 project, the medium and tow-speed magnetic system highlights the green way to solve urban traffic problems.%阐述中低速磁浮系统这一新交通系统的基本原理和特点,提出中低速磁浮系统的适用范围.深圳中低速磁浮8号线项目的应用研究表明,中低速磁浮系统是解决城市交通问题的绿色途径.

  6. Characterization of semiconductor-laser phase noise and estimation of bit-error rate performance with low-speed offline digital coherent receivers.

    Science.gov (United States)

    Kikuchi, Kazuro

    2012-02-27

    We develop a systematic method for characterizing semiconductor-laser phase noise, using a low-speed offline digital coherent receiver. The field spectrum, the FM-noise spectrum, and the phase-error variance measured with such a receiver can completely describe phase-noise characteristics of lasers under test. The sampling rate of the digital coherent receiver should be much higher than the phase-fluctuation speed. However, 1 GS/s is large enough for most of the single-mode semiconductor lasers. In addition to such phase-noise characterization, interpolating the taken data at 1.25 GS/s to form a data stream at 10 GS/s, we can predict the bit-error rate (BER) performance of multi-level modulated optical signals at 10 Gsymbol/s. The BER degradation due to the phase noise is well explained by the result of the phase-noise measurements.

  7. 荧光微丝在低速风洞试验中应用的关键技术研究%Key technologies study of fluorescent mini-tuft application in the low speed wind tunnel tests

    Institute of Scientific and Technical Information of China (English)

    惠增宏; 侯金玉; 邓磊

    2015-01-01

    Fluorescent mini-tuft method is a surface flow visualization technology using mini-tuft with fluorescent material to visualize the flow characteristics under the UV light of specific wavelength.This method can reduce the disturbance of the tufts to the flow and give more accu-rate flow information.In this paper,the key technologies (including the making and sticking method of the mini-tufts,choosing the wavelength of UV lights and taking photos,etc.)of fluo-rescent mini-tuft method are investigated based on a high-lift device wind tunnel test of a certain civil aircraft in NF-3 low speed wind tunnel of NWPU.The results show that,(1)the flow pat-terns at different angles of attack are clear and intuitive,and the developments of the flow states with the angle of attack are shown,(2 )the flow state and range can be easily read in detail from the flow patterns,(3)compared with the fluorescent oil flow tests,the results are relatively sim-ilar under the same experimental conditions.It shows that the fluorescent mini-tuft method can exactly display the flow field.The flow visualization results agree well with the force measure-ment experiments and thus can interpret the force measurement results.%荧光微丝法是将含有荧光物质的直径极小的丝线粘贴布置于模型表面,在紫外线照射下呈现出明显的荧光效果,以此来显示模型表面流场的试验方法,能减小丝线对流场的干扰进而更加真实地反映流场特征。基于在西北工业大学NF-3低速风洞中进行的某大型民机增升装置风洞试验,完成了低速风洞中使用荧光微丝法进行表面流动显示的关键技术研究,包括荧光微丝的制成及粘贴方式、光源的选择及拍摄技术等。模型机翼上表面丝线在不同迎角下的流谱清晰直观、区别明显、易于判读,可较为精细地反映流经翼面的气流状态和范围,并可清晰反映表面流谱随模型姿态角的连续变化情况。同一工

  8. Computed Flow Through An Artificial Heart Valve

    Science.gov (United States)

    Rogers, Stewart E.; Kwak, Dochan; Kiris, Cetin; Chang, I-Dee

    1994-01-01

    Report discusses computations of blood flow through prosthetic tilting disk valve. Computational procedure developed in simulation used to design better artificial hearts and valves by reducing or eliminating following adverse flow characteristics: large pressure losses, which prevent hearts from working efficiently; separated and secondary flows, which causes clotting; and high turbulent shear stresses, which damages red blood cells. Report reiterates and expands upon part of NASA technical memorandum "Computed Flow Through an Artificial Heart and Valve" (ARC-12983). Also based partly on research described in "Numerical Simulation of Flow Through an Artificial Heart" (ARC-12478).

  9. Application of photogrammetry to surface flow visualization

    Energy Technology Data Exchange (ETDEWEB)

    Karthikeyan, N.; Venkatakrishnan, L. [Council of Scientific and Industrial Research, Experimental Aerodynamics Division, National Aerospace Laboratories, Delhi (India)

    2011-03-15

    The construction of three-dimensional surface flow fields is an extremely difficult task owing largely to the fragmented information available in the form of 2D images. Here, the method of photogrammetric resection based on a comprehensive camera model has been used to map oil flow visualization images on to the surface grid of the model. The data exported in the VRML format allow for user interaction in a manner not possible with 2D images. The technique is demonstrated here using the surface oil flow visualization images of a simplified landing gear model at low speed in a conventional wind tunnel without any specialized rigs for photogrammetry. The results are not limited to low-speed regimes and show that this technique can have significant impact on understanding the flow physics associated with the surface flow topology of highly three-dimensional separated flows on complex models. (orig.)

  10. 高阶精度方法下的湍流生成项对低速流动数值模拟的影响研究%High-order numerical analysis of the effect of turbulent production terms on low-speed numerical simulation

    Institute of Scientific and Technical Information of China (English)

    王运涛; 孙岩; 李松; 李伟

    2015-01-01

    Based on the Reynolds-averaged Navier-Stokes(RANS)equations and structured grid technology,the effect of different production terms of SST turbulence model on simulation results of low-speed problems is analyzed numerically with fifth-order weighted compact nonlin-ear scheme(WCNS).The main purpose of present work is to provide technical support for the application of high-order difference schemes in complex configurations.The studied models in-clude low-speed NLR7301 two-element airfoil and Trap wing configuration,the research work contains the influence of different production terms of SST turbulence model on convergence his-tory,the distribution of turbulent viscosity and velocity in boundary layer,pressure coefficients and aerodynamic characters.Compared with experimental data,the numerical results indicate that for low-speed two-dimensional flow,different production terms affect the convergence histo-ry obviously,whereas have little influence on turbulent viscosity and velocity distribution in boundary layer.For the low-speed two-dimensional flow,different production terms affect the suction in the leading edge ,which results in the variation of lift coefficient and pressure-drag co-efficient.For low-speed three-dimensional flow,different production terms have little influence on the convergence history,whereas affect the numerical accuracy of the tip vortex obviously,and then,affect the pressure distribution on the span wing section near the wing tip and aerody-namic characters.%基于雷诺平均的 Navier-Stokes 方程和结构网格技术,采用五阶空间离散精度的 WCNS 格式,开展了 SST两方程模型不同湍流生成项对低速流动数值模拟的计算分析。主要目的是为高阶精度格式在复杂外形上的应用提供技术支撑。计算模型包含了低速 NLR7301两段翼型和 Trap Wing 高升力构型,研究内容主要包括不同湍流生成项对收敛历程、边界层湍流粘性系数分布、边界层速度分

  11. Reduction of relative centrifugation force within injectable platelet-rich-fibrin (PRF) concentrates advances patients' own inflammatory cells, platelets and growth factors: the first introduction to the low speed centrifugation concept.

    Science.gov (United States)

    Choukroun, J; Ghanaati, S

    2017-03-10

    The aim of this study was to analyze systematically the influence of the relative centrifugation force (RCF) on leukocytes, platelets and growth factor release within fluid platelet-rich fibrin matrices (PRF). Systematically using peripheral blood from six healthy volunteers, the RCF was reduced four times for each of the three experimental protocols (I-III) within the spectrum (710-44 g), while maintaining a constant centrifugation time. Flow cytometry was applied to determine the platelets and leukocyte number. The growth factor concentration was quantified 1 and 24 h after clotting using ELISA. Reducing RCF in accordance with protocol-II (177 g) led to a significantly higher platelets and leukocytes numbers compared to protocol-I (710 g). Protocol-III (44 g) showed a highly significant increase of leukocytes and platelets number in comparison to -I and -II. The growth factors' concentration of VEGF and TGF-β1 was significantly higher in protocol-II compared to -I, whereas protocol-III exhibited significantly higher growth factor concentration compared to protocols-I and -II. These findings were observed among 1 and 24 h after clotting, as well as the accumulated growth factor concentration over 24 h. Based on the results, it has been demonstrated that it is possible to enrich PRF-based fluid matrices with leukocytes, platelets and growth factors by means of a single alteration of the centrifugation settings within the clinical routine. We postulate that the so-called low speed centrifugation concept (LSCC) selectively enriches leukocytes, platelets and growth factors within fluid PRF-based matrices. Further studies are needed to evaluate the effect of cell and growth factor enrichment on wound healing and tissue regeneration while comparing blood concentrates gained by high and low RCF.

  12. The computational and experimental investigation on winglets of a low speed aircraft%低速飞机加装翼梢小翼的CFD数值计算及风洞试验研究

    Institute of Scientific and Technical Information of China (English)

    刘毅; 赵晓霞; 江宗辉; 任庆祝

    2015-01-01

    An aircraft with four turbo-propeller engines is characterized by low speed and relative high cruise lift coefficient.Winglets are utilized to improve the flow condition around the wing tips and increase the lift-to-drag ratio.CFD calculation and wind tunnel tests show that the lift-to-drag ratio at endurance cruise can be increased by 8%,while the lift-to-drag ratio at range cruise can be increased by 4.8% after the optimization of geometric parameters.The results of CFD simulation about the aerodynamic characteristics of the winglet agree well with wind tunnel test results, which could be a convenient and economic method for further optimization of winglet geometry.%针对某四发涡桨飞机飞行速度较低,巡航升力系数较大的特点,通过加装翼梢小翼改善翼尖流场特性而提高巡航升阻比。经数值计算和风洞试验验证表明,几何参数优化后的小翼,可以使飞机久航点升阻比提高8%,远航点升阻比提高4.8%。加装翼梢小翼气动特性的CFD数值计算和风洞试验结果吻合良好,可作为小翼外形进一步优化后快捷、经济的验证手段。

  13. Design of axial-flux permanent-magnet low-speed machines and performance comparison between radial-flux and axial-flux machines

    Energy Technology Data Exchange (ETDEWEB)

    Parviainen, A.

    2005-07-01

    This thesis presents an alternative approach to the analytical design of surface-mounted axial-flux permanent-magnet machines. Emphasis has been placed on the design of axial-flux machines with a one-rotor-two-stators configuration. The design model developed in this study incorporates facilities to include both the electromagnetic design and thermal design of the machine as well as to take into consideration the complexity of the permanent-magnet shapes, which is a typical requirement for the design of high-performance permanent-magnet motors. A prototype machine with rated 5 kW output power at 300 min{sup -1} rotation speed has been designed and constructed for the purposes of ascertaining the results obtained from the analytical design model. A comparative study of low-speed axial-flux and low-speed radial-flux permanent-magnet machines is presented. The comparative study concentrates on 55 kW machines with rotation speeds 150 min{sup -1}, 300 min{sup -1} and 600 min{sup -1} and is based on calculated designs. A novel comparison method is introduced. The method takes into account the mechanical constraints of the machine and enables comparison of the designed machines, with respect to the volume, efficiency and cost aspects of each machine. It is shown that an axial-flux permanent-magnet machine with one-rotor-two-stators configuration has generally a weaker efficiency than a radial-flux permanent-magnet machine if for all designs the same electric loading, air-gap flux density and current density have been applied. On the other hand, axial-flux machines are usually smaller in volume, especially when compared to radial-flux machines for which the length ratio (axial length of stator stack vs. air-gap diameter) is below 0.5. The comparison results show also that radial-flux machines with a low number of pole pairs, p < 4, outperform the corresponding axial-flux machines. (orig.)

  14. 低速空降风洞试验的关键技术%Key Techniques of Airborne Tests in Low-speed Wind Tunnel

    Institute of Scientific and Technical Information of China (English)

    惠增宏; 熊超; 张彬乾

    2012-01-01

    低速空降风洞试验的一个重要目的是研究伞降人员在离机初期的运动姿态和空间轨迹,考察伞降人员的离机安全性。从不带伞空降风洞试验出发,分析归纳单次出舱和连续出舱空降风洞试验中的一些关键技术,包括试验方法的选取、相似参数的确定、空降模型的设计加工和调整技术、载机支撑方式和支撑干扰的影响、空降模型出舱姿态的控制、空降轨迹捕获和分析技术等。进而初步探讨带伞空降风洞试验的一些特有问题,旨在为进一步发展低速空降风洞模拟试验技术提供支持。%One important objective of airborne tests in low-speed wind tunnel is to obtain the model's moving posture and motion trajectory of the early stage of the airborne flight to analyze the security of the parachutists. The key techniques of airborne tests in single and continuous separating from the port are summarized based on the airborne test without the parachute on the model. These techniques include the selection of test methods, the determination of similar parameters, the processing and adjustment techniques of airborne models, the mod el support methods and the effect of support interference, the control of airborne models~ moving posture when they separate from the port, the techniques of airborne trajectory capture and analysis, etc. Further more, the problems of airborne tests with parachute on the model are preliminary analyzed with the aim of technique sup- port in further development of airborne tests in low-speed wind tunnel.

  15. An Auto-Tuning PI Control System for an Open-Circuit Low-Speed Wind Tunnel Designed for Greenhouse Technology

    Directory of Open Access Journals (Sweden)

    Karlos Espinoza

    2015-08-01

    Full Text Available Wind tunnels are a key experimental tool for the analysis of airflow parameters in many fields of application. Despite their great potential impact on agricultural research, few contributions have dealt with the development of automatic control systems for wind tunnels in the field of greenhouse technology. The objective of this paper is to present an automatic control system that provides precision and speed of measurement, as well as efficient data processing in low-speed wind tunnel experiments for greenhouse engineering applications. The system is based on an algorithm that identifies the system model and calculates the optimum PI controller. The validation of the system was performed on a cellulose evaporative cooling pad and on insect-proof screens to assess its response to perturbations. The control system provided an accuracy of <0.06 m·s‾1 for airflow speed and <0.50 Pa for pressure drop, thus permitting the reproducibility and standardization of the tests. The proposed control system also incorporates a fully-integrated software unit that manages the tests in terms of airflow speed and pressure drop set points.

  16. Design of Rolling Balance Experimental Equipment for LowSpeed Wind Tunnel%低速风洞旋转天平试验装置的设计

    Institute of Scientific and Technical Information of China (English)

    杨恩霞; 庞永刚; 刁彦飞

    2001-01-01

    By way of simulating trial of plane model whirligig in windtunnel by use of rolling balance and measuring the aerodynamic force on circumvoluting model,we can analyse the trial spinning characteristic.This is one of the efficient way. The paper introduced the working prinnciple and structural design of rolling balance for low speed wind tunnelindetail.%应用旋转天平使飞机模型在风洞里模拟飞机尾旋时的旋转运动,并测量出旋转模型上的气动力,从而对飞机的尾旋特性进行分析、预测,这是研究飞机尾旋特性的有效方法之一。较为详细地介绍了低速风洞旋转天平的工作原理及结构设计。

  17. Production of syngas and oil at biomass refinery and their application in low speed two stroke engines for combined cycle electric energy generation

    Energy Technology Data Exchange (ETDEWEB)

    Pinatti, Daltro Garcia [Universidade do Sul de Santa Catarina (UNISUL), Tubarao, SC (Brazil)], E-mail: pinatti@demar.eel.usp.br; Oliveira, Isaias de; Ferreira, Joao Carlos; Romao, Erica Leonor [RM Materiais Refratarios Ltd., Lorena, SP (Brazil)], Emails: isaias@rm-gpc.com.br, joaocarlos@rm-gpc.com.br, ericaromao@rm-gpc.com.br; Conte, Rosa Ana [University of Sao Paulo (DEMAR/EEL/USP), SP (Brazil). Lorena School of Engineering. Dept. of Materials Engineering], E-mail: rosaconte@demar.eel.usp.br

    2009-07-01

    Low speed two stroke engines burn fuels of medium quality with high efficiency (47%) and allows a flexible use of oil (> 8% of total power) and syngas (< 92%, low heating value-LHV>11.2MJ/m{sup 3}). Biomass refinery (BR) generates oil from sludge and oleaginous biomass by low temperature conversion and syngas from lignocellulosic biomass treated by diluted acidic prehydrolysis. BR has low investment cost (US$1,500.00/kW) compared with hydroelectric plants (US$2,500.00/kW) and both generate electric energy with sales price below US$75.00/MWh. It allows distributed generation from 30 MW up to 170 MW or centralized power of 1 GW with six motor generator sets. BR matrix, mass and energy balance, fuels compositions, modulations and scope of supply will be presented. Besides electric energy BR can be tailored to supply other products such as ethanol, H{sub 2} for fuel cells, biodiesel, fertilizer recycling, char and simultaneously maximizes the production of animal protein. (author)

  18. Experimental studies on the effect of Reynolds and Weber numbers on the impact forces of low-speed droplets colliding with a solid surface

    Science.gov (United States)

    Zhang, Bin; Li, Jingyin; Guo, Penghua; Lv, Qian

    2017-09-01

    The impact force of low-speed droplets colliding with a solid surface was recorded with an experimental setup involving a highly sensitive piezoelectric force transducer and a high-speed camera recording the droplet shape. Water, ethanol, pure glycerin and aqueous glycerin solutions were used. Experimental results showed that dimensionless force is independent of the Weber number in the experimental range of 68-858 but varies with the Reynolds number. The impact is categorized into three types of processes according to the data on dimensionless peak force against the Reynolds number. The first type is a viscosity-dominated one, in which the Reynolds number ranges between 2.9 and 20. In the second type, transition process, the Reynolds number is in the range of 20-230. In the inertia-dominated type, the Reynolds number is larger than 230. In the viscosity-dominated impact, dimensionless peak force decreases rapidly with increasing Reynolds number, and the effect of viscosity could not be ignored. In the inertia-dominated impact, dimensionless peak force remains constant with varying the Reynolds number, that is, impact force is directly proportional to the product of liquid density, velocity squared and diameter squared but is unaffected by the changes in viscosity and surface tension. Furthermore, the deformation of droplet shape due to oscillation affects the impact force; a small horizontal-to-vertical ratio results in small impact force and vice versa.

  19. Motion analysis of human cervical vertebrae and injury mechanisms during low speed rear impacts; Teisokudo tsuitotsu ni okeru ningen no keitsui kyodo kaiseki to shogai mechanism

    Energy Technology Data Exchange (ETDEWEB)

    Ono, K. [Japan Automobile Research Institute Inc., Tsukuba (Japan); Kaneoka, K.; Inami, S.; Hayashi, K. [University of Tsukuba. Tsukuba (Japan)

    1998-05-01

    It is said that, as long as a head rest is used in an automobile, dilation of the cervical vertebrae will not extend the physiological range. However, neck injuries are still occurring frequently as a result of the rear collision accidents. This paper describes an experiment simulating low speed rear impacts by using ten volunteers for the purpose of clarifying the neck injury mechanism. Data taken by using a continuous X-ray photographing device were analyzed. The following points were made clear on features of collisions from comparison with normal cervical vertebral behavior: at a rear impact, the cervical vertebrae are subjected to action of axial compression force due to inertia of the neck, in addition to push-up of the body resulting in upward movement, and the force remains affecting the cervical vertebral behavior thereafter; the effect appears as a bending condition in the cervical vertebrae in the initial stage around 50 to 100 ms after the impact, and then transfers into dilation behavior; and this condition exceeds the normal physiologically movable range, particularly the movement of the winding center being abnormal, which is thought to involve in the mechanism of generating injuries in vertebral joints. 8 refs., 11 figs.

  20. Production of syngas and oil at biomass refinery and their application in low speed two stroke engines for combined cycle electric energy generation

    Energy Technology Data Exchange (ETDEWEB)

    Pinatti, Daltro Garcia [Universidade do Sul de Santa Catarina (UNISUL), Tubarao, SC (Brazil)], E-mail: pinatti@demar.eel.usp.br; Oliveira, Isaias de; Ferreira, Joao Carlos; Romao, Erica Leonor [RM Materiais Refratarios Ltd., Lorena, SP (Brazil)], Emails: isaias@rm-gpc.com.br, joaocarlos@rm-gpc.com.br, ericaromao@rm-gpc.com.br; Conte, Rosa Ana [University of Sao Paulo (DEMAR/EEL/USP), SP (Brazil). Lorena School of Engineering. Dept. of Materials Engineering], E-mail: rosaconte@demar.eel.usp.br

    2009-07-01

    Low speed two stroke engines burn fuels of medium quality with high efficiency (47%) and allows a flexible use of oil (> 8% of total power) and syngas (< 92%, low heating value-LHV>11.2MJ/m{sup 3}). Biomass refinery (BR) generates oil from sludge and oleaginous biomass by low temperature conversion and syngas from lignocellulosic biomass treated by diluted acidic prehydrolysis. BR has low investment cost (US$1,500.00/kW) compared with hydroelectric plants (US$2,500.00/kW) and both generate electric energy with sales price below US$75.00/MWh. It allows distributed generation from 30 MW up to 170 MW or centralized power of 1 GW with six motor generator sets. BR matrix, mass and energy balance, fuels compositions, modulations and scope of supply will be presented. Besides electric energy BR can be tailored to supply other products such as ethanol, H{sub 2} for fuel cells, biodiesel, fertilizer recycling, char and simultaneously maximizes the production of animal protein. (author)

  1. Calibration of the Flow in the Test Section of the Research Wind Tunnel at DST Group

    Science.gov (United States)

    2015-10-01

    recently upgraded the Low Speed Wind Tunnel electrical control and model support systems. UNCLASSIFIED DST-Group-TN-1468 UNCLASSIFIED...1073. Defence Science and Technology Organisation , Melbourne, Australia. Erm, L. P. 2003 Calibration of the flow in the extended test section...of the low-speed wind tunnel at DSTO. DSTO-TR-1384. Defence Science and Technology Organisation , Melbourne, Australia. Erm, L. P. 2015

  2. Vortex flow hysteresis

    Science.gov (United States)

    Cunningham, A. M., Jr.

    1986-01-01

    An experimental study was conducted to quantify the hysteresis associated with various vortex flow transition points and to determine the effect of planform geometry. The transition points observed consisted of the appearance (or disappearance) of trailing edge vortex burst and the transition to (or from) flat plate or totally separated flows. Flow visualization with smoke injected into the vortices was used to identify the transitions on a series of semi-span models tested in a low speed tunnel. The planforms tested included simple deltas (55 deg to 80 deg sweep), cranked wings with varying tip panel sweep and dihedral, and a straked wing. High speed movies at 1000 frames per second were made of the vortex flow visualization in order to better understand the dynamics of vortex flow, burst and transition.

  3. 开口试验段优化设计数值模拟%Numerical Investigation about Optimal Design of Open-Jet Rectangular Test Section in Low Speed Wind Tunnel

    Institute of Scientific and Technical Information of China (English)

    丛成华; 任泽斌; 彭强

    2012-01-01

    为提高某低速风洞开口试验段流场品质,采用计算流体力学方法,结合适当的边界条件,对不同设计方案进行了模拟.数值模拟结果显示:采用集气扩散段能有效提高开口试验段流场均匀性;在试验段入口前加装蜂窝器和阻尼网,对提高试验段流场均匀性和方向场、降低湍流度有重要作用.对试验段尺寸与收集器设计的进一步研究表明,延长试验段前入口区长度、增大试验段口径、改变集气扩散段位置与尺寸都能够有效提高模型区流场品质.通过比较,得出了较为合理的匹配参数,流场指标达到了设计要求.%In order improve flow quality of the specific open-jet test section, the design technology of a cer- tain low speed wind tunnel open-jet test section was studied using computational fluid dynamics (CFD). It presents the control equations and boundary conditions for numerical simulation. Then the details of nu- merical results about the different configurations were given. Comparing with full open-jet test section, the velocity uniformity of model region is evidently improved by use of collector. Honeycomb and screens have profound function on the velocity field such as uniformity, direction field and turbulence level. Further in- vestigation on the size of test section and collector indicates that the flow quality of model region is signifi- cantly improved when several measures are implemented such as extending the entrance length before test section, increasing the test section caliber and the changing location and size of the collector. Combination of satisfactory parameters, which can produce a more uniform velocity profile to arrive at the expected lev- el, was obtained based on numerical results.

  4. Study on the Optimum Service Braking System for Low-speed Goods Vehicle%低速货车配备行车制动系统的研究

    Institute of Scientific and Technical Information of China (English)

    马恩; 杨博竣

    2016-01-01

    Current condition of service braking system for low-speed goods vehicle in China are discussed. Service brake safety properties of low-speed goods vehicle are affected directly by service brake system. To ex-plore the optimum designs of service braking system for low-speed goods vehicle, tests were carried out in ac-cordance with GB7258-2012 safety specifications for power-driven vehicles operating on roads. Research and practice in a long period proves the optimum designs are service manual hydraulic braking system for load less than one ton low-speed goods vehicle, but are service power pneumatic braking system for load more than one ton low-speed goods vehicle.%论述了我国低速货车配备行车制动系统的现状,低速货车行车制动系统直接影响其行车安全,试验按照强制性国家标准GB7258-2012《机动车运行安全技术条件》进行,经过研究人员长期研究和实践证明,得到最佳方案是:载重量小于1t的低速货车配备行车人力液压制动系统;载重量大于1t的低速货车配备行车动力气压制动系统。

  5. Highly turbulent solutions of the Lagrangian-averaged Navier-Stokes alpha model and their large-eddy-simulation potential.

    Science.gov (United States)

    Pietarila Graham, Jonathan; Holm, Darryl D; Mininni, Pablo D; Pouquet, Annick

    2007-11-01

    We compute solutions of the Lagrangian-averaged Navier-Stokes alpha - (LANS alpha ) model for significantly higher Reynolds numbers (up to Re approximately 8300 ) than have previously been accomplished. This allows sufficient separation of scales to observe a Navier-Stokes inertial range followed by a second inertial range specific to the LANS alpha model. Both fully helical and nonhelical flows are examined, up to Reynolds numbers of approximately 1300. Analysis of the third-order structure function scaling supports the predicted l3 scaling; it corresponds to a k-1 scaling of the energy spectrum for scales smaller than alpha. The energy spectrum itself shows a different scaling, which goes as k1. This latter spectrum is consistent with the absence of stretching in the subfilter scales due to the Taylor frozen-in hypothesis employed as a closure in the derivation of the LANS alpha model. These two scalings are conjectured to coexist in different spatial portions of the flow. The l3 [E(k) approximately k-1] scaling is subdominant to k1 in the energy spectrum, but the l3 scaling is responsible for the direct energy cascade, as no cascade can result from motions with no internal degrees of freedom. We demonstrate verification of the prediction for the size of the LANS alpha attractor resulting from this scaling. From this, we give a methodology either for arriving at grid-independent solutions for the LANS alpha model, or for obtaining a formulation of the large eddy simulation optimal in the context of the alpha models. The fully converged grid-independent LANS alpha model may not be the best approximation to a direct numerical simulation of the Navier-Stokes equations, since the minimum error is a balance between truncation errors and the approximation error due to using the LANS alpha instead of the primitive equations. Furthermore, the small-scale behavior of the LANS alpha model contributes to a reduction of flux at constant energy, leading to a shallower energy

  6. Photoacoustic Doppler effect from flowing small light-absorbing particles.

    Science.gov (United States)

    Fang, Hui; Maslov, Konstantin; Wang, Lihong V

    2007-11-01

    From the flow of a suspension of micrometer-scale carbon particles, the photoacoustic Doppler shift is observed. As predicted theoretically, the observed Doppler shift equals half of that in Doppler ultrasound and does not depend on the direction of laser illumination. This new physical phenomenon provides a basis for developing photoacoustic Doppler flowmetry, which can potentially be used for detecting fluid flow in optically scattering media and especially low-speed blood flow of relatively deep microcirculation in biological tissue.

  7. Algorithm of brush short-circuit coefficients of DC machines for extremely low speed drives%极低速驱动用直流电机电刷短路系数的算法

    Institute of Scientific and Technical Information of China (English)

    张琪; 谢国栋; 黄苏融

    2008-01-01

    When a direct-current (DC) machine runs at extremely low speed or standstill, the reduction in the armature resistance and the armature flux linkage due to the short circuited coils by the brushes on the commutator should not be neglected. Taking this reduction effect into account, the average values of the reduction coefficients relate to the machine parameters in complicated forms. In this paper, an effective algorithm for the precise computation of the average values of these reduction coefficients is proposed. Furthermore, in the algorithm, the effect of the insulation thickness between the commutator segments and the multiplicity of the wave winding are considered for the first time. The proposed algorithm can also be accommodated into the computer-aided design (CAD) of a DC machine, which normally runs at extremely low speed or standstill.

  8. 浅析企业中低速磁浮交通系统技术标准体系构建%the shallow analysis of construction of technical standards system for enterprise low-speed maglev transportation

    Institute of Scientific and Technical Information of China (English)

    屈蕾

    2016-01-01

    This paper introduces the principle and working procedure of the construction of technical standards system for enter-prise low-speed maglev transportation ,in order to improve enterprise technical standard system,to guarantee the design of ma-glev products"rule-based",to support the application of low-speed maglev project in company.%介绍了企业中低速磁浮交通系统技术标准体系构建的原则和工作程序,旨在完善企业技术标准体系,保证公司磁浮产品设计“有章可循”,为公司中低速磁浮应用项目建设起到支撑作用。

  9. Pre-treatment of waste fuel with low-speed shredding and screening for fluidized bed incineration; Foerbehandling av avfallsbraensle foer fluidbaeddpannor med laangsamtgaaende valskross och saekerhetssiktning

    Energy Technology Data Exchange (ETDEWEB)

    Hermansson, Sven; Victoren, Anders; Niklasson, Fredrik; Jones, Frida

    2013-09-01

    In FB combustion of waste, an important cost factor is the pre-treatment of the waste fuel. The most common method of final levigation of the waste fuel is using hammer mills, which crushes the fuel with high force and high rotational speed. The advantage of the powerful hammer mill is, however, also a disadvantage. The fraction of fines becomes large, and the method is experienced to cause high maintenance costs and problems with accidental fires. A plausible alternative to the hammer mill is the shredder. The rotational speed of the shreeder is lower, while it cutting and slicing the waste fuel instead of grinding it. The shredder is, therefore, expected to yield less wear and tear, lower electricity consumption and less accidental fires. On the other hand, the shreeder may yield a higher fraction of oversized fuel particles, which could cause problems in the combustion, especially in smaller FB-plants with one single fuel supply conveyor. In this project, the framing of question has been if low-speed shredding in combination with screening of over sizes fuel particles, may function for smaller FB plants with one single fuel supplying conveyor. The aim of the project has been to support FB plant owners and manufacturers for independent comparision of the different fuel pre-treatment methods, via pre-treatment and combustions trials and economical comparisons. The concept of lowspeed shreddning and screening has been compared economically with a traditional hammer mill system and a shredding system designed for a larger FB plant. Moreover, combustion trials have been carried out with shredded and screened fuel, and hammer milled fuel, in two smaller parallel FB furnaces with one single fuel supplying conveyor per furnace. The fuels were analysed for particle size distribution and composition, and the operation during the combustion trial was evaluated. The economical evaluation of the new pre-treatment concept, with lowspeed shredding and screening, yielded an

  10. Swirling flow in a two-stroke marine diesel engine

    DEFF Research Database (Denmark)

    Hemmingsen, Casper Schytte; Ingvorsen, Kristian Mark; Walther, Jens Honore

    2013-01-01

    Computational fluid dynamic simulations are performed for the turbulent swirling flow in a scale model of a low-speed two-stroke diesel engine with a moving piston. The purpose of the work is to investigate the accuracy of different turbulence models including two-equation Reynolds- Averaged Navier...

  11. Study on Key Maintenance Equipment for Mid and Low Speed Maglev Train%中低速磁浮列车运用检修关键工艺设备研究

    Institute of Scientific and Technical Information of China (English)

    李经伟; 龙建兵

    2016-01-01

    以国内第一座磁浮车辆段的应用为例,通过对中低速磁浮列车悬浮原理、构造进行分析,研究中低速磁浮列车的维修要点。并结合车辆维修要点,分析适用于磁浮列车运用检修的轨道桥、悬浮架拆装小车、悬浮架综合实验台等关键工艺设备,为今后磁浮车辆段设备的设计提供有益参考。%Taking the fi rst maglev train depot in China for an example the paper studies the main features of maintenance for mid and low-speed maglev train through analyzing the principle and structure. Based on the main factors of train maintenance, it explores the key maintenance equipment for mid and low-speed maglev train, including track bridge, dismantling and assembly trolley with suspension frame and integrated test bench, providing references for the design of equipment for future mid and low speed maglev train.

  12. Influence of piston position on the scavenging and swirling flow in two-stoke diesel engines

    DEFF Research Database (Denmark)

    Obeidat, Anas; Haider, Sajjad; Meyer, Knud Erik

    2011-01-01

    We study the eect of piston position on the in-cylinder swirling flow in a low speed large two-stroke marine diesel engine model. We are using Large Eddy Simulations in OpenFOAM, with three different models for the turbulent flow: a one equation model (OEM), a dynamic one equation model (DOEM...

  13. Serpentine Geometry Plasma Actuators for Flow Control

    Science.gov (United States)

    2013-08-23

    electrical power is supplied to them. As a method of introducing perturbations for low speed flow control, dielectric barrier discharge ( DBD ) actuators...SERPENTINE GEOMETRY DBD ACTUATORS DBD actuators are devices consisting of two asymmetri- cally placed actuators separated by a dielectric material and exposed...parameters can be found in Table I. The effects of plasma actuation are FIG. 1. (a) Schematic of DBD plasma actuator and the generated body force. (b

  14. 小展弦比飞翼标模纵航向气动特性低速实验研究%Low speed experiment on longitudinal and lateral aerodynamic characteristics of the low aspect ratio flying wing calibration model

    Institute of Scientific and Technical Information of China (English)

    吴军飞; 秦永明; 黄湛; 魏忠武; 贾毅

    2016-01-01

    对小展弦比飞翼气动布局外形,通过常规测力风洞实验方法得到其纵向气动特性和偏航控制特性,在分析其气动特性后,选取典型的状态采用 PIV 实验方法对其流动机理进行研究,研究表明小展弦比飞翼在较小的迎角下即出现前缘分离涡,随着迎角的增大,前缘分离涡强度增大,且逐渐往机体对称面方向移动,随着迎角进一步增大,分离涡变得不稳定,涡核开始摆动,最终破裂,破裂位置从后缘开始,逐渐前移。对小展弦比飞翼气动布局飞机的控制难点偏航控制进行研究,结果表明该飞翼布局模型在实验迎角范围内偏航方向是静稳定的,在小迎角下具有可操纵性,迎角大于6°后嵌入面处于破裂的前缘涡尾迹之中,操纵性降低。%longitudinal and lateral aerodynamic characteristics of the low aspect ratio flying wing calibration model are investigated in a low speed wind tunnel.Normal force measuring ex-periment is conducted to gain the longitudinal aerodynamic characteristics and yaw control charac-teristics,and the PIV test is also conducted to investigate the flow mechanism of the low aspect ratio flying wing.The results indicate that the leading-edge separation vortex appears on the wing’s spine surface when the attack angle is at 6 degree.The vortex intensity increases and the vortex core shifts to the symmetric plane of flying wing with the increase of attack angle.Increas-ing the attack angle further,the vortex core becomes unsteady and begins to oscillate,finally break entirely.The broken position shifts from the ending edge to the leading edge.Yaw control characteristics of low aspect ratio flying wing is also studied in this paper.The results indicate that the flying wing is static stabile at the test attack angle.When the attack angle is less than 6 degree,it is controllable in yaw direction.And when attack angle is more than 6 degree,the yaw control

  15. Formation of hybrid gold nanoparticle network aggregates by specific host-guest interactions in a turbulent flow reactor

    NARCIS (Netherlands)

    Weinhart-Mejia, R.; Huskens, Jurriaan

    2014-01-01

    A multi-inlet vortex mixer (MIVM) was used to investigate the formation of hybrid gold nanoparticle network aggregates under highly turbulent flow conditions. To form aggregates, gold nanoparticles were functionalized with β-cyclodextrin (CD) and mixed with adamantyl (Ad)-terminated

  16. Formation of hybrid gold nanoparticle network aggregates by specific host-guest interactions in a turbulent flow reactor

    NARCIS (Netherlands)

    Mejia Ariza, Raquel; Huskens, Jurriaan

    2014-01-01

    A multi-inlet vortex mixer (MIVM) was used to investigate the formation of hybrid gold nanoparticle network aggregates under highly turbulent flow conditions. To form aggregates, gold nanoparticles were functionalized with β-cyclodextrin (CD) and mixed with adamantyl (Ad)-terminated poly(propyleneim

  17. Unified Kinetic Approach for Simulation of Gas Flows in Rarefied and Continuum Regimes

    Science.gov (United States)

    2007-06-01

    a low-speed flow induced by temperature gradients. The nonuniform boundary temperature distribution can induce flows in reactor : a significant flow...Rotational Spectrum and Molecular Interaction Potential, ibid R. R. Arslanbekov and V. I. Kolobov, Simulation of Low Pressure Plasma Processing Reactors ... Microchannel flow in the slip regime: gas-kinetic BGK—Burnett solutions, J. Fluid Mech. 513, 87 (2004) 59 R.L.Bayut, PhD thesis, MIT 1999 60

  18. Average-passage flow model development

    Science.gov (United States)

    Adamczyk, John J.; Celestina, Mark L.; Beach, Tim A.; Kirtley, Kevin; Barnett, Mark

    1989-01-01

    A 3-D model was developed for simulating multistage turbomachinery flows using supercomputers. This average passage flow model described the time averaged flow field within a typical passage of a bladed wheel within a multistage configuration. To date, a number of inviscid simulations were executed to assess the resolution capabilities of the model. Recently, the viscous terms associated with the average passage model were incorporated into the inviscid computer code along with an algebraic turbulence model. A simulation of a stage-and-one-half, low speed turbine was executed. The results of this simulation, including a comparison with experimental data, is discussed.

  19. Computational fluid dynamics incompressible turbulent flows

    CERN Document Server

    Kajishima, Takeo

    2017-01-01

    This textbook presents numerical solution techniques for incompressible turbulent flows that occur in a variety of scientific and engineering settings including aerodynamics of ground-based vehicles and low-speed aircraft, fluid flows in energy systems, atmospheric flows, and biological flows. This book encompasses fluid mechanics, partial differential equations, numerical methods, and turbulence models, and emphasizes the foundation on how the governing partial differential equations for incompressible fluid flow can be solved numerically in an accurate and efficient manner. Extensive discussions on incompressible flow solvers and turbulence modeling are also offered. This text is an ideal instructional resource and reference for students, research scientists, and professional engineers interested in analyzing fluid flows using numerical simulations for fundamental research and industrial applications. • Introduces CFD techniques for incompressible flow and turbulence with a comprehensive approach; • Enr...

  20. Estimation of Power Spectrum Density Track Irregularities of Low-speed Maglev Railway Lines%低速磁浮轨道不平顺功率谱研究

    Institute of Scientific and Technical Information of China (English)

    张耿; 李杰; 杨子敬

    2011-01-01

    Track irregularity is the main excitation source to vibration of the maglev train, and it has direct influence on stability and ride quality of the train. The statistical specimens of track irregularities are collected from the TangShan low-speed maglev experimental line on the basis of the stationarity tests of the specimens, the Fast Fourier Transform(FFT) method was used to evaluate the spectra of the whole specimen space. Distribution of track irregularities in space wavelengths was found. Analysis results show that the structural parameters, installation precision and rolling technique of tracks are the main causes of track irregularity. Referring to the mature PSD( power spectrum density) expressions published athome and abroatl, the set fitting formulas of PSD for low-speed maglev railway lines were proposed. The parameter values of PSD fitting curves for low-speed maglev track irregularities were obtained by use of the damping curve-fitting algorithm in the least-squares sense. Significaul reference is provided to study on track irregularity PSD of low-speed maglev railway lines.%轨道不平顺是磁浮列车振动的主要激扰源,直接关系到列车运行的稳定性和舒适性.文章基于唐山低速磁浮试验线实测的轨道不平顺数据,采用周期图法进行样本空间的谱估计,得到轨道不平顺在各空间波长的分布.分析结果表明,轨道本身结构参数、轨道安装精度和F轨的轧制工艺是产生轨道不平顺的主要原因.参考国内外成熟的铁路轨道谱线表达形式,得到低速磁浮轨道谱的拟合曲线公式,应用阻尼最小二乘算法拟合轨道谱表达式的参数,对于研究我国磁浮轨道不平顺功率谱有重要的参考价值.

  1. CONTINUOUS WAVELET TRANSFORM OF TURBULENT BOUNDARY LAYER FLOW

    Institute of Scientific and Technical Information of China (English)

    LIU Ying-zheng; KE Feng; CHEN Han-ping

    2005-01-01

    The spatio-temporal characteristics of the velocity fluctuations in a fully-developed turbulent boundary layer flow was investigated using hotwire. A low-speed wind tunnel was established. The experimental data was extensively analyzed in terms of continuous wavelet transform coefficients and their auto-correlation. The results yielded a potential wealth of information on inherent characteristics of coherent structures embedded in turbulent boundary layer flow. Spatial and temporal variations of the low- and high- frequency motions were revealed.

  2. Low-Speed Wind-Tunnel Investigation of a Reflection Plane Wing Model Equipped with Partial-Span Jet-Augmented Flaps

    Science.gov (United States)

    Otis, James H., Jr.

    1961-01-01

    An investigation to determine the aerodynamic and flow-field characteristics of three 50-percent partial-span jet-augmented flap configurations located at three spanwise positions has been conducted in the Langley 300 MPH 7- by 10-foot tunnel. The model was a semispan, rectangular unswept wing with a full-span aspect ratio of 8.3 and a thickness-to-chord ratio of 0.167. The results of this investigation showed that an inboard partial-span jet-augmented flap is less effective than a full-span blowing flap. A further reduction in effectiveness is obtained as the blaring is shifted outboard along the span. At a given lift coefficient and angle of attack, the nose-down moment about the quarter chord increases as the blowing is moved outboard. This increase in nose-down moment is due primarily to the fact that the momentum coefficient must be increased in order to obtain the same lift condition. Flow surveys indicate that the tail contribution to static longitudinal stability would be greater for the outboard blowing locations.

  3. High-loading low-speed fan study. 4: Data and performance with redesign stator and including a rotor tip casing treatment

    Science.gov (United States)

    Harley, K. G.; Odegard, P. A.; Burdsall, E. A.

    1972-01-01

    A single stage fan with a rotor tip speed of 1000 ft/sec(304.8 m/sec) and a hub-to-tip ratio of 0.392 was retested with a redesigned stator. Tests were conducted with uniform inlet, tip-radial, hub-radial, and circumferential inlet distortions. With uniform inlet flow, stall margin was improved 12 percentage points above that with the original stator. The fan demonstrated an efficiency of 0.883 and a stall margin of 15 percent at a pressure ratio of 1.488 and a specific flow of 41.17 lb/sec/sq ft. Tests were also made with a redesigned casing treatment consisting of skewed slots over the rotor blade tips. This casing treatment gave a 7 percentage point improvement in stall margin when tested with tip radial distortion (when the rotor tip initiated stall). Noise measurements at the fan inlet and exit indicate no effect from closing the stator 10 degrees, nor were there measurable effects from adding skewed slots over the blade tips.

  4. Experimental and Numerical Optimization of a High-Lift System to Improve Low-Speed Performance, Stability, and Control of an Arrow-Wing Supersonic Transport

    Science.gov (United States)

    Hahne, David E.; Glaab, Louis J.

    1999-01-01

    An investigation was performed to evaluate leading-and trailing-edge flap deflections for optimal aerodynamic performance of a High-Speed Civil Transport concept during takeoff and approach-to-landing conditions. The configuration used for this study was designed by the Douglas Aircraft Company during the 1970's. A 0.1-scale model of this configuration was tested in the Langley 30- by 60-Foot Tunnel with both the original leading-edge flap system and a new leading-edge flap system, which was designed with modem computational flow analysis and optimization tools. Leading-and trailing-edge flap deflections were generated for the original and modified leading-edge flap systems with the computational flow analysis and optimization tools. Although wind tunnel data indicated improvements in aerodynamic performance for the analytically derived flap deflections for both leading-edge flap systems, perturbations of the analytically derived leading-edge flap deflections yielded significant additional improvements in aerodynamic performance. In addition to the aerodynamic performance optimization testing, stability and control data were also obtained. An evaluation of the crosswind landing capability of the aircraft configuration revealed that insufficient lateral control existed as a result of high levels of lateral stability. Deflection of the leading-and trailing-edge flaps improved the crosswind landing capability of the vehicle considerably; however, additional improvements are required.

  5. Joule-Thomson effect and internal convection heat transfer in turbulent He II flow

    Science.gov (United States)

    Walstrom, P. L.

    1988-01-01

    The temperature rise in highly turbulent He II flowing in tubing was measured in the temperature range 1.6-2.1 K. The effect of internal convection heat transport on the predicted temperature profiles is calculated from the two-fluid model with mutual friction. The model predictions are in good agreement with the measurements, provided that the pressure gradient term is retained in the expression for internal convection heat flow.

  6. Joule-Thomson effect and internal convection heat transfer in turbulent He II flow

    Science.gov (United States)

    Walstrom, P. L.

    1988-03-01

    The temperature rise in highly turbulent He II flowing in tubing was measured in the temperature range 1.6-2.1 K. The effect of internal convection heat transport on the predicted temperature profiles is calculated from the two-fluid model with mutual friction. The model predictions are in good agreement with the measurements, provided that the pressure gradient term is retained in the expression for internal convection heat flow.

  7. New devices for flow measurements: Hot film and burial wire sensors, infrared imagery, liquid crystal, and piezo-electric model

    Science.gov (United States)

    Mcree, Griffith J., Jr.; Roberts, A. Sidney, Jr.

    1991-01-01

    An experimental program aimed at identifying areas in low speed aerodynamic research where infrared imaging systems can make significant contributions is discussed. Implementing a new technique, a long electrically heated wire was placed across a laminar flow. By measuring the temperature distribution along the wire with the IR imaging camera, the flow behavior was identified.

  8. Two-Phase Cavitating Flow in Turbomachines

    Directory of Open Access Journals (Sweden)

    Sandor I. Bernad

    2012-11-01

    Full Text Available Cavitating flows are notoriously complex because they are highly turbulent and unsteady flows involving two species (liquid/vapor with a large density difference. These features pose a unique challenge to numerical modeling works. The study briefly reviews the methodology curently employed for industrial cavitating flow simulations using the two-phase mixture model. The two-phase mixture model is evaluated and validated using benchmark problem where experimental data are available. A 3D cavitating flow computation is performed for the GAMM Francis runner. The model is able to qualitatively predict the location and extent of the 3D cavity on the blade, but further investigation are needed to quatitatively assess the accuracy for real turbomachinery cavitating flows.

  9. 中低速磁悬浮列车远程维护管理系统研究%The Research on Remote Maintenance Management System of Mid-low Speed Maglev Train

    Institute of Scientific and Technical Information of China (English)

    包清政; 窦峰山; 龙志强

    2011-01-01

    This paper developed an in-depth study of the planning, analysts, design and engineering implementation of the remote maintenance management system for mid-low speed maglev train. According to the demands of Tangshan mid-low speed maglev train testing line and the practic requirement of S1 line in Belling, the general plan of the whole system was accomplished and a development scheme based on C/S architecture combining with NET framework and SQL Server data-base system was proposed, which realized the comprehensive design of all aspects of the system and was into practice.%围绕中低速磁悬浮列车远程维护管理系统的规划、分析、设计与工程实现工作,进行了深入的研究.结合唐山中低速磁悬浮试验基地的特点和北京S1线的实际需求,完成了系统的总体规划,提出了采用C/S体系结构、结合NET开发平台和SQL Server数据库系统的技术方案,实现了对系统的全面设计并应用于实践.

  10. Electromagnetic Operation Environment Analysis of Middle-low-speed Maglev Train%中低速磁悬浮列车运行电磁环境的分析

    Institute of Scientific and Technical Information of China (English)

    齐洪峰

    2012-01-01

    With electromagnetic finite element method, leakage magnetic field distribution of electromagnets and linear traction motor was simulated and calculated, the results of which were compared to test reports of electromagnetic radiation field of CMS04 middle-low-speed maglev train carried out by Institute of Electrical Engineering Chinese Academy of Science, which proved that middle-low-speed maglev train transport system was a kind of green urban rail transit system with good electromagnetic environment.%采用电磁场有限元法对悬浮电磁铁和直线牵引电机的泄漏磁场分布进行仿真计算,并将计算结果与中国科学院电工所对CMS04型中低速磁悬浮列车电磁辐射现场测试报告进行详实的比较分析,从而证明了中低速磁悬浮列车交通系统是一种电磁环境良好的绿色城市轨道交通系统.

  11. Multistage Turbomachinery Flows Simulated Numerically

    Science.gov (United States)

    Hathaway, Michael D.; Adamczyk, John J.; Shabbir, Aamir; Wellborn, Steven R.

    1999-01-01

    At the NASA Lewis Research Center, a comprehensive assessment was made of the predictive capability of the average passage flow model as applied to multistage axial-flow compressors. This model, which describes the time-averaged flow field within a typical passage of a blade row embedded in a multistage configuration, is being widely used throughout U.S. aircraft industry as an integral part of their design systems. Rotor flow-angle deviation. In this work, detailed data taken within a four and one-half stage large low-speed compressor were used to assess the weaknesses and strengths of the predictive capabilities of the average passage flow model. The low-speed compressor blading is of modern design and employs stator end-bends. Measurements were made with slow- and high response instrumentation. The high-response measurements revealed the velocity components of both the rotor and stator wakes. From the measured wake profiles, we found that the flow exiting the rotors deviated from the rotor exit metal angle to a lesser degree than was predicted by the average passage flow model. This was found to be due to blade boundary layer transition, which recently has been shown to exist on multistage axial compressor rotor and stator blades, but was not accounted for in the average passage model. Consequently, a model that mimics the effects of blade boundary layer transition, Shih k-epsilon model, was incorporated into the average passage model. Simulations that incorporated this transition model showed a dramatic improvement in agreement with data. The altered model thus improved predictive capability for multistage axial-flow compressors, and this was verified by detailed experimental measurement.

  12. 中低速磁浮交通工程建设核心技术研究%Research on the Core Technology of Engineering Construction for Medium and Low Speed Maglev Transit

    Institute of Scientific and Technical Information of China (English)

    徐银光; 蔡文锋

    2015-01-01

    研究目的:纵观国内外,在中低速磁浮交通工程建设的实践中尽管取得了很大的进展,但仍有很多重难点技术,需要系统地进行梳理并加以研究解决,从而为工程建设和安全营运提供系统全面的技术支撑,推动我国中低速磁浮交通的发展。  研究结论:(1)中低速磁浮交通由于其自身特点和技术优势,是中低运量城市地面轨道交通的最佳制式,在我国有广阔的应用前景;(2)提出了中低速磁浮交通工程建设中需要深入开展的七项核心技术:车、轨、桥、设备及建筑耦合关系研究,线路、轨道技术研究,供输电技术研究,信号技术研究,运营维护及故障救援研究,地面交通与城市和谐关系研究以及磁浮对特殊环境的影响研究;(3)该研究成果可为中低速磁浮交通勘测设计、施工及运营维护提供指导。%Research purposes:Throughout the practice at home and abroad in the medium and low speed maglev transit engineering construction in spite of the great progress has been made,but there are still a lot of difficult point technologies need to systematically comb and study to solve,which can provide comprehensive technical support system for the engineering construction and safety operation,promote the development of the medium and low speed maglev transit in our country. Research conclusions:(1 )The medium and low speed maglev transit due to its own characteristics and technical advantages,is the best type of low ground traffic city track traffic,has a broad application prospect in our country. (2)This paper put forward seven core technologies of the medium and low speed maglev transit engineering construction which need to be intensified:coupling relationship research among the vehicle,rail,bridge,equipment and building, lines and rail technology research,transmission technology research, signal technology research, operation and maintenance and

  13. Design, manufacture and construction of a compressor test rig and the start of experimental operation of a low speed axial compressor at Dresden. Final report; Konstruktion, Fertigung und Aufbau eines Verdichterpruefstandes und Aufnahme des Versuchsbetriebes an einem Niedergeschwindigkeits-Axialverdichter in Dresden. Abschlussbericht

    Energy Technology Data Exchange (ETDEWEB)

    Bernstein, W.; Bernhard, H.; Biesinger, T.; Boos, P.; Moeckel, H.; Sauer, H.

    1996-12-01

    In this report, the design, manufacture and construction of the low speed compressor, the build-up of the compressor test rig and the measurement technique used are described. The first measured results obtained after setting to work and the start of experimental operation on the rotational symmetry at the compressor inlet and outlet and of a flow field behind the rotor and stator of the third stage are described. The operating period of 540 hours to the end of the subject shows faultfree operation of the experimental plant. (orig./AKF) [Deutsch] Im vorliegenden Bericht werden Konstruktion, Fertigung und Aufbau des Niedergeschwindigkeitsverdichters, der Aufbau des Verdichterpruefstandes und die verwendete Messtechnik beschrieben. Die nach der Inbetriebnahme und Aufnahme des Versuchsbetriebes erhaltenen ersten Messergebnisse zur Rotationssymmetrie am Ein- und Austritt des Verdichters und von einem Stroemungsfeld hinter dem Rotor und Stator der dritten Stufe werden geschildert. Die zum Abschluss des Themas erreichte Betriebszeit von 540 Stunden weist auf einen stoerungsfreien Betrieb der Versuchsanlage hin. (orig./AKF)

  14. Secondary flow, turbulent diffusion and mixing in axial-flow compressors

    Science.gov (United States)

    Wisler, D. C.; Bauer, R. C.; Okiishi, T. H.

    1987-05-01

    The relative importance of convection by secondary flows and diffusion by turbulence as mechanisms responsible for mixing in multistage, axial-flow compressors has been investigated by using the ethylene tracer-gas technique and hot wire anemometry. The tests were conducted at two loading levels in a large, low-speed, four-stage compressor. The experimental results show that considerable cross-passage and spanwise fluid motion can occur and that both secondary flow and turbulent diffusion can play important roles in the mixing process, depending upon location in the compressor and loading level.

  15. Travelling-waves consistent with turbulence-driven secondary flow in a square duct

    CERN Document Server

    Uhlmann, Markus; Pinelli, Alfredo; 10.1063/1.3466661

    2010-01-01

    We present numerically determined travelling-wave solutions for pressure-driven flow through a straight duct with a square cross-section. This family of solutions represents typical coherent structures (a staggered array of counter-rotating streamwise vortices and an associated low-speed streak) on each wall. Their streamwise average flow in the cross-sectional plane corresponds to an eight vortex pattern much alike the secondary flow found in the turbulent regime.

  16. 某款车用发电机低速噪声源的识别与控制%Identification and Reduction of the Noise Source of a Vehicle's Generator Operation in Low Speed Range

    Institute of Scientific and Technical Information of China (English)

    石晓辉; 昌诗力; 施全; 易鹏

    2015-01-01

    针对某款车用发电机低速噪声偏大的问题,首先进行发电机台架噪声试验,运用阶次分析找到主要特征阶次.采用数值模拟和试验验证相结合的方法对车用发电机结构进行模态分析,计算出发电机的前几阶固有频率与模态振型.结合噪声试验分析结果与模态特性,得出低速噪声偏大是由于发电机在电磁力波的激励下发生了共振的结论.最后提出改进建议,改进后的电机低速下噪声得到明显的改善,总体声压级降低约2 dB(A),共振处声压级降低约5 dB(A).%The problem of overlarge noise of a vehicle's generator operating in low speed range was studied. Firstly, the noise was tested in a test bench and the main orders of the noise were found by order analysis. Secondly, both numerical simulation and experimental test were applied to the modal analysis of the vehicle's generator, and the natural frequencies and vibration modes of the previous orders of the vehicle's generator were calculated. Thirdly, through the comprehensive analysis of the test results of noise and the modal characteristics, it was concluded that the overlarge noise in low speed range was caused by the generator's resonance inspired by electromagnetic force wave. Finally, some improvement suggestions were provided and the noise of the vehicle's generator operating in low speed range was reduced distinctly, the overall noise dropped by 2 dB(A), and the noise in the resonance point dropped by 5 dB(A).

  17. Effect of Low-speed Treadmill Training on Hemiplegic Patients after Stroke%慢速活动平板训练对脑卒中偏瘫患者下肢功能的影响

    Institute of Scientific and Technical Information of China (English)

    李立; 刘建华; 张辉; 杜水英

    2011-01-01

    目的 探讨慢速活动平板训练对脑卒中偏瘫患者下肢功能的影响.方法 脑卒中偏瘫患者26例分成治疗组14例及对照组12例.两组患者均给予常规康复训练,治疗组在此基础上进行3个月慢速活动平板训练.分别于治疗前后进行Fugl-Meyer运动功能评定(FMA)、Berg平衡量表(BBS)评定,10m最大步行速度、自由步行速度及6min步行距离测定.结果 治疗后,两组患者FMA、BBS评分,10m最大步行速度、自由步行速及6 min步行距离均比治疗前提高(P<0.05),治疗组FMA、BBS评分,10m自由步行速度及6 min步行距离优于对照组(P<0.05).结论 慢速活动平板训练能改善脑卒中偏瘫患者步行功能及平衡能力.%Objective To investigate the effect of low-speed treadmill training on function of lower limbs in hemiplegic patients after stroke. Methods 26 hemiplegic patients after stroke were divided into the treatment group (n=14) and control group (n=12). Both groups accepted routine rehabilitation, and the treatment group accepted low-speed treadmill training in addition. They were evaluated with Fugl-Mey-er Assessment (FMA), Berg Balance Scale (BBS), 6-min walk distance, 10-m walking speed before and after treatment. Results The scores of FMA and BBS, and the distance of 6-min walk, speed of 10-m walking improved in both groups (P<0.05), and improved more in the treatment group than in the control group (P<0.05) after 3-mouth treatment. Conclusion Low-speed treadmill training can significantly improve walk ability and balance function of the hemiplegic patients after stroke.

  18. Flow analysis of vortex generators on wing sections by stereoscopic particle image velocimetry measurements

    DEFF Research Database (Denmark)

    Velte, Clara Marika; Hansen, Martin Otto Laver; Cavar, Dalibor

    2008-01-01

    Stereoscopic particle image velocimetry measurements have been executed in a low speed wind tunnel in spanwise planes in the flow past a row of vortex generators, mounted on a bump in a fashion producing counter-rotating vortices. The measurement technique is a powerful tool which provides all...

  19. 超低速直流电机电刷短路系数计算%Computation of brush short-circuit coefficients of DC machines for extremely low speed drives

    Institute of Scientific and Technical Information of China (English)

    张琪; 谢国栋; 黄苏融

    2006-01-01

    Short circuit due to the brushes over the commutator segments of DC machines causes reduction in the armature resistance and flux linkage, which is especially meaningful when the electric machine is running at zero or extremely low speed. In design computation of DC machines, usually the average values of the coefficients are used in consideration of the effects of the short circuit.However, the average values have complicated relationships with the parameters of electric machines, therefore, no usable mathematical model has been established yet for precise computation. In this paper, a relatively simple and generalized method for precise computation of the average values of the short-circuit coefficients is proposed. This method decouples some of the machine parameters and, therefore establishes a highly parameterized mathematical model and is convenient in formulation for computation. In addition, the computation data for one and two brush pairs, which are the most common cases, is provided.

  20. Control strategy research on the electronic control system of the marine low-speed diesel engine%船用低速柴油机电控系统控制策略试验研究

    Institute of Scientific and Technical Information of China (English)

    王勤鹏; 杨建国; 余永华

    2013-01-01

    为研究电控系统主要控制参数随柴油机负荷变化规律及各参数间的相互关联,利用船用低速柴油机高压共轨电控系统硬件在环仿真试验平台,同步采集试验平台重要控制参数,对电控系统燃油轨压调节、伺服油轨压调节、低负荷喷油器轮换工作、燃油喷射定时和排气阀启闭定时等控制策略进行了研究。研究表明:燃油轨压调节采用闭环和前馈修正的控制算法,喷射定时控制与柴油机转速、扫气压力和燃油轨压相关联,柴油机低负荷时3个喷油器按一定间隔时间轮换工作;随柴油机负荷增加,伺服油轨压和排气阀开启持续角度亦增加;排气阀开启与柴油机转速和排气关闭角度相关,而排气阀关闭则仅与柴油机转速相关。%In order to research the law of the main control parameters of the electronic control system changing with diesel engine loads, as well as correlation of parameters, the control strategy of the high-pressure common-rail elec-tronic control system for a marine low-speed diesel engine is presented in this paper. Based on a hardware-in-loop simulation test bench, the important control parameters of the test bench were collected synchronically to research the fuel rail pressure control of the electronic control system, servo oil rail pressure control, low load injector rotation law, the injection timing and the exhaust valve start and stop timing, etc. The research results show that the common-rail fuel pressure is regulated by using a closed-loop and a correction of a feed-forward control algorithm. The injection timing control is affected by the rotation speed of the marine low-speed diesel engine, the scavenging pressure and the fuel common-rail pressure. Three injectors in a cylinder work alternately with a certain interval time at low loads of the marine low-speed diesel engine. With the increase of the load of the marine diesel engine, the servo oil

  1. 钢纤维-钢筋混凝土板抗低速冲击作用机理研究%Reinforcing Mechanism of Steel - Fiber -Reinforced Concrete Slabs against Low Speed Impact

    Institute of Scientific and Technical Information of China (English)

    秦菱; 王鹏飞; 童云罡

    2015-01-01

    主要从纤维强化理论、板壳理论和防护结构计算理论等3个方面,分别阐述了钢纤维-钢筋混凝土板构件在低速冲击作用下的强化原理,重点解释了钢纤维的增韧机理、薄板小挠度弯曲理论和弹性体系结构的动力分析方法.%This paper illustrates the reinforcing mechanism of steel -fiber -reinforced concrete slabs against low speed impact from the fiber reinforcing theory,the theory of plates and shells,and the protective structure calculation theory. It mainly explains the reinforcing mechanism of steel fiber,small deflection bending theory of thin slabs and dynamic analysis theory of elastic system structure.

  2. A crossed hot-wire technique for complex turbulent flows

    Science.gov (United States)

    Cutler, A. D.; Bradshaw, P.

    1991-01-01

    This paper describes a crossed hot-wire technique for the measurement of all components of mean velocity, Reynolds stresses, and triple products in a complex turbulent flow. The accuracy of various assumptions usually implicit in the use of crossed hot-wire anemometers is examined. It is shown that significant errors can result in flow with gradients in mean velocity or Reynolds stress, but that a first-order correction for these errors can be made using available data. It is also shown how corrections can be made for high turbulence levels using available data.

  3. Numerical predictions of hydrodynamic forces on a ship during a low-speed drift motion in shallow water including verification and validation%浅水中低速斜航船舶水动力预报及验证与确认分析

    Institute of Scientific and Technical Information of China (English)

    邹璐

    2016-01-01

    Travelling at a drift angle in shallow water, the ship is affected by both the asymmetry flow and the blockage from shallow water. To predict the hydrodynamic forces on the ship, this paper applies a Com-putational Fluid Dynamics method based on the steady state Reynolds-Averaged Navier-Stokes equations to solve the viscous flow around the ship during a low-speed drift motion in shallow water. Considering the ship moves at a low speed, the effects of free surface are assumed negligible. Tendencies of the hydrody-namic forces against the drift angle are simulated from numerical computations. For the purpose of evaluat-ing the degree of accuracy in the numerical results, verification and validation analyses are performed. The numerical error and uncertainty are estimated from a grid convergence study, while the modelling errors are investigated along with the experimental data. In addition, the contributions of computational domain size, turbulence model, boundary condition, as well as the influence of sinkage and trim to the modelling errors are discussed. This study offers a useful reference for the improvement of the numerical model and the ac-curacy in numerical predictions.%浅水中的斜航船舶受到浅水阻塞效应和不对称流的综合影响。为预报该运动中的船舶水动力,文章采用基于定常雷诺平均纳维—斯托克斯方程的计算流体动力学方法,对浅水中做斜航运动的船舶粘性绕流场进行数值模拟。考虑低航速运动的特点,忽略航速影响下的自由面兴波,由数值计算得到水动力系数在漂角影响下的变化规律。针对计算精度问题,在数值模拟中从验证和确认角度分析和评估计算结果:通过网格收敛性分析分析数值误差与不确定度;结合试验数据考察计算模型的误差。此外,从计算区域尺度、湍流模型、边界条件、船体下沉和纵倾作用方面对模型误差的影响因素进行探讨,可为改进

  4. 低速风洞全模TPS试验空气桥的设计与优化%Design and optimization of the air bridge for low speed full-span TPS test

    Institute of Scientific and Technical Information of China (English)

    章荣平; 王勋年; 黄勇; 冯治

    2012-01-01

    TPS(Turbofan Powered Simulator)technology is the most advanced engine simulation in wind tunnel test. The air bridge is a key technology of TPS tests. This paper presents the design of the air bridge for low speed full-span TPS test. Optimum designs are made for the key beams of the air bridge by using FEM (finite-element method). Layout and the dimension of bellows are also optimized. According to the computation results, the key law of air bridge design is concluded. The air bridge is finally designed according to the space of the model, the inside e-quipments and the requirement of the TPS test. The final design has little effect on force measurement and has little pressure and temperature effect. The success in low speed full-span TPS test indicates that the air bridge meet the requirement of TPS test.%TPS试验技术是目前风洞试验中最先进的涡扇发动机模拟技术,空气桥是TPS试验技术的关键技术之一.介绍了低速全模TPS试验空气桥的设计.通过有限元数值模拟对空气桥关键受力梁进行了优化设计,并进一步对空气桥进行了整体优化,掌握了关键参数影响空气桥性能的规律.综合考虑模型内部空间、内部设备及空气桥的技术要求,完成了空气桥的设计,优化后空气桥对天平测力的影响较小,且同时具有较好的克服高压空气的内力、温度效应的能力.试验结果表明,空气桥性能满足TPS试验的要求.

  5. 永磁同步电机静止及低速下无传感器控制研究%Sensorless Control of Permanent Magnet Synchronous Motor at Zero Speed and Low Speed

    Institute of Scientific and Technical Information of China (English)

    干瑞; 朱元; 王双全

    2012-01-01

    In order to achieve the estimation of rotor position of IPMSM at low speed and zero speed, a scheme based on high frequency injection method for sensorless control of permanent magnet synchronous motor was presented. The basic principal of high frequency injection method was discussed combined with the mathematical model of PMSPM in detail. In consideration of the magnetically saturated saliency, the high frequency response character of PMSM was studied, based on which a new method extracting the DC component of high frequency current was proposed for distinguishing the rotor polarity at zero speed. The impact and compensation of phase deviation of high frequency current was also discussed. The experiment result shows that the methods adopted have satisfies performance at both zero speed and low speed.%研究了一种基于高频注入法的永磁同步电机无传感器控制技术,以实现内埋式永磁同步电机在静止及低速下转子位置的估算.结合电机数学模型阐述了脉振注入法的原理.利用电机的饱和凸极性,分析了电机在静止时的高频响应特性,并提出了一种通过提取高频电流直流分量来判断电机转子极性的方法.为r解决响应电流存在相位偏移的问题,将d轴高频电流作为输入量,通过锁相环得到响应电流的相位偏移值,并做出相应的补偿.实验结果表明,采用的方法跟踪性能良好,适用于电机的静止以及低速运行阶段.

  6. 船舶电力推进DTC系统低速性能的改善研究%The Improvement Study of Low Speed Performance in Ship Electric Propulsion DTC System

    Institute of Scientific and Technical Information of China (English)

    李彦; 唐智星

    2013-01-01

    针对船舶电力推进传统直接转矩控制(DTC)技术低速性能差的问题,引入模糊控制对定子电阻进行在线辨识.引入空间矢量脉宽调剂技术(SVPWM)来减低转矩与电流的脉动;并且使开关频率得到固定.另外由于船舶推进时易受外界干扰的影响,导致基于固定PI参数的速度调节器不能实时跟踪动态的外界环境干扰,因此引入模糊自适应PID对速度调节器进行动态整定.仿真结果表明引入模糊控制和空间矢量脉宽调剂技术后,低速性能及动态性能得到显著改善.%According to the poor performance at low speed in ship electric propulsion traditional DTC technology, including the stator flux distort,caused by influence of stator resistance in U-I flux observation model; torque and current ripple is bigger. The unfixed switching frequency makes the switching loss and noise incrensed. Thus, the fuzzy control is introduced to online identify stator resistance, and adopt SVM technology to reduce torque and current ripple. It also makes the switch frequency fixed. Besides,because of ship propulsion is susceptible to external interference effect, that result based on a fixed PI parameters of the speed regulator can not be real-time tracking dynamic environment'interference. So, the method of fuzzy adaptive PID is adapted to dynamic set the parameters. The simulation in matlab/simulink results show that the low speed performance and dynamic performance can be improved significantly after fuzzy control and SVM technology are adapted.

  7. 螺旋压力机实现伺服直驱的低速大力矩电动机综述%A survey of low speed large torque motor for driving the screw press

    Institute of Scientific and Technical Information of China (English)

    梁锦涛; 赵升吨; 谢嘉

    2011-01-01

    Various types of low speed large torque motors which are used to drive screw press have been introduced in the text. The structure, working principle,advantages & disadvantages,and domestic & foreign research status have been shown respectively. Finally, several important factors which should be considered in the design process of the motor for driving the screw press have been put forward.%实现伺服直驱是现代螺旋压力机的重要发展方向之一.本文对用于螺旋压力机伺服直驱的各类低速大力矩电动机进行了介绍,阐述其基本结构、工作原理、优缺点以及国内外研究现状.最后提出设计螺旋压力机直驱式电动机需要考虑的几个因素.

  8. The Medium and Low Speed Maglev Train -Track Beam Coupling Vibration Model and Verification%中低速磁浮列车-轨道梁竖向耦合模型与验证

    Institute of Scientific and Technical Information of China (English)

    李小珍; 洪沁烨; 耿杰; 刘德军; 单春胜

    2015-01-01

    研究目的:在我国新建中低速磁浮运营线的背景下,因中低速磁浮轨道梁较为轻巧,为保证磁浮列车行车安全及舒适性,需对其进行磁浮列车-轨道梁耦合振动分析验证。本文以株洲某厂磁浮试验线20 m 简支梁为工程背景,建立车辆为12个自由度的二系悬挂质量-弹簧-阻尼模型,并考虑轨道不平顺对车桥振动的影响,建立磁浮列车-轨道梁竖向耦合振动分析模型,且编制仿真分析软件 VTBIM,通过仿真值与现场试验实测值的对比,验证所建模型的合理性。研究结论:(1)现场试验测试轨道梁基频、振型及轨道梁跨中动挠度/加速度,轨道梁基频及振型测试结果比仿真值略小;(2)磁浮车辆通过简支梁时,梁跨中竖向挠度/加速度的实测值均略小于仿真值,仿真值随车速的变化规律与实测值规律一致,挠度时程曲线仿真值与实测波形基本一致;(3)研究结果表明本文所建立的中低速磁浮列车-轨道梁竖向耦合振动模型合理,编制的仿真分析软件的计算结果可信;(4)该研究结果可用于中低速磁浮轨道梁设计参考。%Research purposes:In our country under the background of new construction of medium and low speed maglev operation,because the low speed maglev rail beam is relatively light,in order to ensure the safety and comfort,the maglev train -track beam coupling vibration should be analyzed and verified.Based on the engineering background of 20 m simply supported beam of maglev test line in a factory of Zhuzhou,this paper establishes the secondary suspension quality -spring - damper model that vehicle is 12 degrees of freedom,builds maglev trains and track beam vertical coupling vibration analysis model considering the impact of track irregularity,and designs the simulation analysis software VTBIM.Through comparing the simulation value with the measured values

  9. Vertical Dynamics Analysis of Levitation Chassis on Middle and Low Speed Maglev Vehicle%中低速磁浮列车悬浮架垂向动力学分析

    Institute of Scientific and Technical Information of China (English)

    周益; 刘放; 李贤坤; 迟振华

    2012-01-01

    Based on the viberation of bouncing, pitching and rolling directions, the vertical dynamics model of levitation chassis was established, and the equations of motion of the model were derived. A simulation program was designed to simulate the vibration dynamic characteristics of the levitation chassis for a certain latest middle and low speed maglev vehicle. The structure decoupling function of levitation chassis was further studied, especially the influence of elastic constraints between the maglev vehicle specific left and right module, and evidences were provided for designing the restraint parameters of module rolling.%建立了考虑沉浮、点头、侧滚多方向振动的悬浮架垂向动力学模型,编制了系统动力学仿真程序,分析了某新型中低速磁浮悬浮架的振动动态特性;进一步研究了悬浮架结构解耦,特别是磁浮车辆特有的左右模块之间弹性约束的影响,为磁浮车辆抗侧滚悬挂参数设计提供依据.

  10. Flow tilt angles near forest edges - Part 1: Sonic anemometry

    DEFF Research Database (Denmark)

    Dellwik, Ebba; Mann, Jakob; Larsen, Klaus Steenberg

    2010-01-01

    -sets. These features of the investigated sonic anemometers make them unsuitable for measuring vertical velocities over highly turbulent forested terrain. By comparing the sonic anemometer results to that of a conically scanning Doppler lidar (Dellwik et al., 2010b), sonic anemometer accuracy for measuring mean flow...... distortion and vertical alignment, it was only possible to a limited extent to relate sonic anemometer flow tilt angles to upwind forest edges, but the results by the lidar indicated that an internal boundary layer affect flow tilt angles at 21m above the forest. This is in accordance with earlier studies......An analysis of flow tilt angles from a fetch-limited beech forest site with clearings is presented in the context of vertical advection of carbon dioxide. Flow angles and vertical velocities from two sonic anemometers by different manufacturers were analyzed. Instead of using rotations, where zero...

  11. EXPERIMENT STUDY ON SEDIMENT INCIPIENCE IN BACKWARD- FACING STEP FLOW

    Institute of Scientific and Technical Information of China (English)

    LIU Chun-rong; Huhe Aode; TAO Long-bin

    2007-01-01

    Flow over a backward-facing step was studied to investigate the effect of large-scale vortex structures on sediment incipience. The transient flow velocity field at the downstream of the backward-facing step was obtained using the technique of Particle Tracking Velocimetry (PTV). The optical amplification technique was employed to measure the instantaneous flow velocities near the bed and the instantaneous bed shear stress was given. The experimental observations revealed a new insight into the oscillation of the large-scale structure and the three-dimensional characteristics of the flow. In particular, very high turbulence intensity, instantaneous horizontal velocity near the bed and the bed shear stress near the reattachment point were observed. The sediment incipient probability obtained from the sequent images of sediment particles near the bed indicates that the critical instantaneous shear stress of the sediment incipience is independent of flow conditions.

  12. Turbulent characteristics of shear-thinning fluids in recirculating flows

    Energy Technology Data Exchange (ETDEWEB)

    Pereira, A.S. [Inst. Superior de Engenharia do Porto (Portugal). Dept. de Engenharia Quimica; Pinho, F.T. [Centro de Estudos de Fenomenos de Transporte, Departamento de Engenharia Mecanica e Gestao Industrial, Faculdade de Engenharia da Universidade do Porto, Rua dos Bragas, 4050-123 Porto (Portugal)

    2000-03-01

    A miniaturised fibre optic laser-Doppler anemometer was used to carry out a detailed hydrodynamic investigation of the flow downstream of a sudden expansion with 0.1-0.2% by weight shear-thinning aqueous solutions of xanthan gum. Upstream of the sudden expansion the pipe flow was fully-developed and the xanthan gum solutions exhibited drag reduction with corresponding lower radial and tangential normal Reynolds stresses, but higher axial Reynolds stress near the wall and a flatter axial mean velocity profile in comparison with Newtonian flow. The recirculation bubble length was reduced by more than 20% relative to the high Reynolds number Newtonian flow, and this was attributed to the occurrence further upstream of high turbulence for the non-Newtonian solutions, because of advection of turbulence and earlier high turbulence production in the shear layer. Comparisons with the measurements of Escudier and Smith (1999) with similar fluids emphasized the dominating role of inlet turbulence. The present was less anisotropic, and had lower maximum axial Reynolds stresses (by 16%) but higher radial turbulence (20%) than theirs. They reported considerably longer recirculating bubble lengths than we do for similar non-Newtonian fluids and Reynolds numbers. (orig.)

  13. Aerodynamic Effects of High Turbulence Intensity on a Variable-Speed Power-Turbine Blade With Large Incidence and Reynolds Number Variations

    Science.gov (United States)

    Flegel, Ashlie B.; Giel, Paul W.; Welch, Gerard E.

    2014-01-01

    The effects of high inlet turbulence intensity on the aerodynamic performance of a variable speed power turbine blade are examined over large incidence and Reynolds number ranges. These results are compared to previous measurements made in a low turbulence environment. Both high and low turbulence studies were conducted in the NASA Glenn Research Center Transonic Turbine Blade Cascade Facility. The purpose of the low inlet turbulence study was to examine the transitional flow effects that are anticipated at cruise Reynolds numbers. The current study extends this to LPT-relevant turbulence levels while perhaps sacrificing transitional flow effects. Assessing the effects of turbulence at these large incidence and Reynolds number variations complements the existing database. Downstream total pressure and exit angle data were acquired for 10 incidence angles ranging from +15.8deg to -51.0deg. For each incidence angle, data were obtained at five flow conditions with the exit Reynolds number ranging from 2.12×10(exp 5) to 2.12×10(exp 6) and at a design exit Mach number of 0.72. In order to achieve the lowest Reynolds number, the exit Mach number was reduced to 0.35 due to facility constraints. The inlet turbulence intensity, Tu, was measured using a single-wire hotwire located 0.415 axial-chord upstream of the blade row. The inlet turbulence levels ranged from 8 to 15 percent for the current study. Tu measurements were also made farther upstream so that turbulence decay rates could be calculated as needed for computational inlet boundary conditions. Downstream flow field measurements were obtained using a pneumatic five-hole pitch/yaw probe located in a survey plane 7 percent axial chord aft of the blade trailing edge and covering three blade passages. Blade and endwall static pressures were acquired for each flow condition as well. The blade loading data show that the suction surface separation that was evident at many of the low Tu conditions has been eliminated. At

  14. Flow Mapping of a Jet in Crossflow with Stereoscopic PIV

    DEFF Research Database (Denmark)

    Meyer, Knud Erik; Özcan, Oktay; Westergaard, C. H.

    2002-01-01

    Stereoscopic Particle Image Velocimetry (PIV) has been used to make a three-dimensional flow mapping of a jet in crossflow. The Reynolds number based on the free stream velocity and the jet diameter was nominally 2400. A jet-to-crossflow velocity ratio of 3.3 was used. Details of the formation...... of the counter rotating vortex pair found behind the jet are shown. The vortex pair results in two regions with strong reversed velocities behind the jet trajectory. Regions of high turbulent kinetic energy are identified. The signature of the unsteady shear layer vortices is found in the mean vorticity field....

  15. Reduction of relative centrifugal forces increases growth factor release within solid platelet-rich-fibrin (PRF)-based matrices: a proof of concept of LSCC (low speed centrifugation concept).

    Science.gov (United States)

    El Bagdadi, K; Kubesch, A; Yu, X; Al-Maawi, S; Orlowska, A; Dias, A; Booms, P; Dohle, E; Sader, R; Kirkpatrick, C J; Choukroun, J; Ghanaati, S

    2017-03-21

    Purpose The present study evaluated the platelet distribution pattern and growth factor release (VEGF, TGF-β1 and EGF) within three PRF (platelet-rich-fibrin) matrices (PRF, A-PRF and A-PRF+) that were prepared using different relative centrifugation forces (RCF) and centrifugation times. Materials and methods immunohistochemistry was conducted to assess the platelet distribution pattern within three PRF matrices. The growth factor release was measured over 10 days using ELISA. Results The VEGF protein content showed the highest release on day 7; A-PRF+ showed a significantly higher rate than A-PRF and PRF. The accumulated release on day 10 was significantly higher in A-PRF+ compared with A-PRF and PRF. TGF-β1 release in A-PRF and A-PRF+ showed significantly higher values on days 7 and 10 compared with PRF. EGF release revealed a maximum at 24 h in all groups. Toward the end of the study, A-PRF+ demonstrated significantly higher EGF release than PRF. The accumulated growth factor releases of TGF-β1 and EGF on day 10 were significantly higher in A-PRF+ and A-PRF than in PRF. Moreover, platelets were located homogenously throughout the matrix in the A-PRF and A-PRF+ groups, whereas platelets in PRF were primarily observed within the lower portion. ​Discussion the present results show an increase growthfactor release by decreased RCF. However, further studies must be conducted to examine the extent to which enhancing the amount and the rate of released growth factors influence wound healing and biomaterial-based tissue regeneration. ​Conclusion These outcomes accentuate the fact that with a reduction of RCF according to the previously LSCC (described low speed centrifugation concept), growth factor release can be increased in leukocytes and platelets within the solid PRF matrices.

  16. Parameter analysis and optimal design for low-speed permanent magnet wind turbine generators%低速永磁风力发电机的参数分析及优化设计

    Institute of Scientific and Technical Information of China (English)

    何庆领; 王群京

    2011-01-01

    文章讨论了低速永磁同步风力发电机的设计特点,为了有效地减少阻力矩,采用分数槽绕组,为减少漏磁通,采用瓦片型和放射状的永磁体安装结构,并重点对结构参数与运行性能之间的内在关系进行了参数分析,为风力发电机本体的优化设计打下基础.在一定安装尺寸的限制下,以电机效率作为优化目标,采用基于混沌理论的最优化算法获取风力发电机的最大输出效率.%This paper discusses the design characteristics of low-speed permanent magnet synchronous wind turbine generator, including the use of fractional slot windings to effectively reduce the resistance moment, the use of tiles and reflective-like structure to reduce leakage flux,and the installation of permanent magnet The intrinsic relationship between structural parameters and operational performance is also analyzed for the optimal design of wind turbine foundation. Aiming at optimizing the motor efficiency, the optimization algorithm based on chaos theory can be used to obtain the maximum output efficiency of wind turbine generator under a certain restriction of installation size.

  17. Simulation and Performance Optimization of a Car under Low-speed Rear End Impacts%某车型后端低速碰撞的安全性能分析及优化

    Institute of Scientific and Technical Information of China (English)

    崔淑娟; 陈可明; 史爱民; 符志; 李气辉

    2016-01-01

    A FE model of a car under low-speed rear end impacts was established according to the regulation of GB17354—1998, and it was found that the protective performance of the rear bumper did not meet the requirements. An improved rear bumper design based on experience was proposed which satisfies the requirements of the regulation; however, it may not be the best solution. To further optimize the improved structure, an adaptive response surface method was adopted in which the material thicknesses of key components were designated as design variables, the weight of the components as an objective function and the second order response surface approximation model was established. The result indicates that the optimized solution meets the requirements of the regulation and the weight of the bumper system is reduced by 22.7%.%根据 GB 17354—1998法规要求对某车型进行了低速后碰撞的仿真分析,结果不满足法规要求。针对分析结果提出了一种改进方案,经过分析,采用新方案的车型满足法规性能要求。但基于经验的设计方案并不能代表最优解,以影响后端碰撞性能的关键组件材料厚度为设计变量,质量为目标函数,建立了二阶响应面近似模型,并选用自适应响应面法(Adaptive Response Surface Method,ARSM)进行优化,优化后质量减轻了22.7%,并且满足法规要求。

  18. Flow Control Device Evaluation for an Internal Flow with an Adverse Pressure Gradient

    Science.gov (United States)

    Jenkins, Luther N.; Gorton, Susan Althoff; Anders, Scott G.

    2002-01-01

    The effectiveness of several active and passive devices to control flow in an adverse pressure gradient with secondary flows present was evaluated in the 15 Inch Low Speed Tunnel at NASA Langley Research Center. In this study, passive micro vortex generators, micro bumps, and piezoelectric synthetic jets were evaluated for their flow control characteristics using surface static pressures, flow visualization, and 3D Stereo Digital Particle Image Velocimetry. Data also were acquired for synthetic jet actuators in a zero flow environment. It was found that the micro vortex generator is very effective in controlling the flow environment for an adverse pressure gradient, even in the presence of secondary vortical flow. The mechanism by which the control is effected is a re-energization of the boundary layer through flow mixing. The piezoelectric synthetic jet actuators must have sufficient velocity output to produce strong longitudinal vortices if they are to be effective for flow control. The output of these devices in a laboratory or zero flow environment will be different than the output in a flow environment. In this investigation, the output was higher in the flow environment, but the stroke cycle in the flow did not indicate a positive inflow into the synthetic jet.

  19. Statistical parameters of thermally driven turbulent anabatic flow

    Science.gov (United States)

    Hilel, Roni; Liberzon, Dan

    2016-11-01

    Field measurements of thermally driven turbulent anabatic flow over a moderate slope are reported. A collocated hot-films-sonic anemometer (Combo) obtained the finer scales of the flow by implementing a Neural Networks based in-situ calibration technique. Eight days of continuous measurements of the wind and temperature fluctuations reviled a diurnal pattern of unstable stratification that forced development of highly turbulent unidirectional up slope flow. Empirical fits of important turbulence statistics were obtained from velocity fluctuations' time series alongside fully resolved spectra of velocity field components and characteristic length scales. TKE and TI showed linear dependence on Re, while velocity derivative skewness and dissipation rates indicated the anisotropic nature of the flow. Empirical fits of normalized velocity fluctuations power density spectra were derived as spectral shapes exhibited high level of similarity. Bursting phenomenon was detected at 15% of the total time. Frequency of occurrence, spectral characteristics and possible generation mechanism are discussed. BSF Grant #2014075.

  20. The turbulent flow generated by inhomogeneous multiscale grids

    Science.gov (United States)

    Zheng, Shaokai; Bruce, Paul J. K.; Graham, J. Michael R.; Vassilicos, John Christos

    2015-11-01

    A group of inhomogeneous multiscale grids have been designed and tested in a low speed wind tunnel in an attempt to generate bespoke turbulent shear flows. Cross-wire anemometry measurements were performed in different planes parallel to the grid and at various streamwise locations to study turbulence development behind each of the different geometry grids. Two spatially separated single hot wires were also used to measure transverse integral length scale at selected locations. Results are compared to previous studies of shearless mixing layer grids and fractal grids, including mean flow profiles and turbulence statistics.

  1. Analysis of anelastic flow and numerical treatment via finite elements

    Energy Technology Data Exchange (ETDEWEB)

    Martinez, M.J.

    1994-05-01

    In this report, we reconsider the various approximations made to the full equations of motion and energy transport for treating low-speed flows with significant temperature induced property variations. This entails assessment of the development of so-called anelastic for low-Mach number flows outside the range of validity of the Boussinesq equations. An integral part of this assessment is the development of a finite element-based numerical scheme for obtaining approximate numerical solutions to this class of problems. Several formulations were attempted and are compared.

  2. PIV Study of the Effect of Piston Motion on the Confined Swirling Flow in the Scavenging Process in 2-Stroke Marine Diesel Engines

    DEFF Research Database (Denmark)

    Haider, Sajjad; Meyer, Knud Erik; Schramm, Jesper

    2010-01-01

    The effect of piston motion on the incylinder swirling flow for a low speed, large two-stroke marine diesel engine is studies using the stereoscopic PIV technique. The measuremenrs are conducted at 5 cross sectional planes along the cylinder length and at piston positions covering the air intake...

  3. PIV study of the effect of piston position on the in-cylinder swirling flow during the scavenging process in large two-stroke marine diesel engines

    DEFF Research Database (Denmark)

    Haider, Sajjad; Schnipper, Teis; Obeidat, Anas

    2013-01-01

    A simplified model of a low speed large twostroke marine diesel engine cylinder is developed. The effect of piston position on the in-cylinder swirling flow during the scavenging process is studied using the stereoscopic particle image velocimetry technique. The measurements are conducted...

  4. Helical structure of longitudinal vortices embedded in turbulent wall-bounded flow

    DEFF Research Database (Denmark)

    Velte, Clara Marika; Hansen, Martin Otto Laver; Okulov, Valery

    2009-01-01

    Embedded vortices in turbulent wall-bounded flow over a flat plate, generated by a passive rectangular vane-type vortex generator with variable angle \\beta to the incoming flow in a low-Reynolds number flow (Re = 2600 based on the inlet grid mesh size L = 0:039 m and free stream velocity U......_{\\infty} = 1.0 ms^{-1}) have been studied with respect to helical symmetry. The studies were carried out in a low-speed closed-circuit wind tunnel utilizing Stereoscopic Particle Image Velocimetry (SPIV). The vortices have been shown to possess helical symmetry, allowing the flow to be described in a simple...

  5. Finite element analysis of the spreader of the low speed marine diesel engine%低速船用柴油机整机吊具可靠性的有限元分析

    Institute of Scientific and Technical Information of China (English)

    马哲树; 渠满菊; 蒋爱民

    2013-01-01

    船用低速柴油机的吊具受力复杂且不规则,传统设计通过简化模型计算其理论强度,与实际工况误差较大。文中利用有限元软件ANSYS分析,以6S42MC整机吊具为研究对象,采用三维软件PROE建立该吊具模型并对其进行有限元分析,根据分析所得的应力分布和形变情况,判断吊具的可靠性;通过改变吊具的结构尺寸,对减少吊具应力的方法进行探究;对吊具进行拓扑优化。分析结果表明,文中方法可以检验吊具的安全性,提高经济效益,同时为吊具的理论设计提供了依据。%The forces acted on the low-speed marine diesel engines′spreader are complex and irregular .The tra-ditional design calculates the theoretical strength by simplifying the model ,but it has great errors under the actual working conditions .In this paper ,by using finite element software ANSYS analysis ,we make up for the defects of the traditional design .Model and finite element analysis are mode by the three-dimensional software PROE .Ac-cording to analysis from the stress distribution and deformation ,the reliability of the spreader is judged;the reduc-tion of the stress of the spreader is explored by changing the structure size of the spreader ;the topology optimiza-tion is made .The analysis results proved that we can test the safety of the spreader ,improve the econanic benefit , and provide the basis for the theory of the spreader design .

  6. 低速磁浮交通轨道结构强度计算与分析%Strength Calculation and Analysis on Track Structure for Low-speed Maglev Transit

    Institute of Scientific and Technical Information of China (English)

    朱晓嘉; 赵春发; 庞玲; 蔡文锋

    2012-01-01

    结合株洲机车厂低速磁浮试验线工程,建立了包含F形导轨、H形轨枕、混凝土轨道梁及其联接件的磁浮线路上部结构有限元模型,计算了列车悬浮静荷载、悬浮动荷载以及列车滑撬和滑轮支承荷载作用下轨道结构的应力与变形,并依据相关标准和规范对轨道结构设计进行校核.结果表明:低速磁浮轨道的导轨、轨枕、M16和M30螺栓均满足其强度设计要求;为了提高F形导轨与轨枕的联接强度,降低F形导轨两磁极反应面的垂向位移差,可适当加大导轨与轨枕连接螺栓的直径.%In combination with the low-speed maglev test-line project on the CSR Zhuzhou Electric Locomotive Co. , LTD. , a finite element model of track superstructures including the F-shaped lead rail, the H-shaped sleeper, the concrete girder and all the fastenings is developed. Then stress responses and deformations of the track structure are calculated under the train static levitation loads, dynamic levitation loads, skid loads and supporting pulley loads. Furthermore, the track structure strength is checked according to relevant design guidelines and standards. Analysis results show that the rail, the sleeper, the M16 and M30 bolts meet the strength design requirements. In order to enhance the joint strength between the lead rail and the sleeper, and decreasing the vertical displacement difference between both magnetic pole response surfaces of F-shaped rail, the nominal diameter of bolt linking the rail and sleeper should be increased properly.

  7. 径向低速大扭矩水液压马达定子曲线分析%Analysis of stator curve of low speed high torque water hydraulic motor with radial piston

    Institute of Scientific and Technical Information of China (English)

    高殿荣; 王志强; 温茂森; 吴晓明

    2011-01-01

    提出了一种采用自然水(含海水和淡水)作为液压介质进行工作的径向低速大扭矩马达.与油压马达相比,摩擦、磨损、腐蚀等是水压马达面临的主要问题,而合适的定子曲线可以减少摩擦、磨损、水击等现象的发生.本文根据运动学理论对水液压马达的定子曲线进行了设计与分析.对幅角修正等加速运动规律和匀变加速修正等加速运动规律的加速度公式进行了修正.对9种不同类型运动规律的各区段幅角进行了设计,并结合曲线方程和水压马达的相关参数绘制出相应的定子曲线.综合分析了9种类型定子曲线下柱塞副(滚球与柱塞)的加速度、速度以及曲线压力角等特性,指出有过渡区的等加速运动规律曲线较适合于所研究的低速大扭矩水液压马达.%A novel low speed high torque hydraulic motor with radial piston, using seawater and fresh water as the hydraulic medium, is presented. Compared with hydraulic motor, friction, wear and corrosion are the main problems to be concerned. However, the friction, the wear and the water hammer could be reduced using the optimal stator curve. The stator curve of this motor is designed and analyzed based on the kinematics. The acceleration formulae of revised argument equal-acceleration motion and uniform variable accelerated modifier are revised. Every zone of argument of nine different motions is designed. On the basis of curve equations and hydraulic motor parameters, the stator curves are got. The acceleration, velocity of piston pairs (roller and piston) and pressure angle of nine stator curves are comprehensively analyzed. Results show that the transition region equal-acceleration motion curve is suitable for this motor.

  8. Application of Using Ultra-Low-Speed Die Casting the Support Bracket of Automobile Engine Transmission%汽车发动机变速箱支架类零件的超低速压铸工艺

    Institute of Scientific and Technical Information of China (English)

    刘春生; 苏建强; 罗金祺

    2013-01-01

    针对传统压铸工艺在生产超厚型产品时存在的气孔率高、强度低等问题,研究开发了某发动机支架零件的超低速压铸工艺,讨论了不同压射速度、内浇口厚度、浇注温度以及模具结构和模温控制等因素对压铸产品质量的影响.结果表明,当低速压射速度为0.25 m/s,高速压射速度为0.5 m/s,内浇口厚度为5.2 mm,浇注温度为680~690℃时,获得的铸件质量最好.通过对超低速压铸模具结构进行改进,并采用顺序凝固模温控制方法,满足了对铸件进行T6热处理的要求,使产品性能有较大提升.%aiming at problems existed in the traditional die casting super-thickness product, such as high porosity, low strength, the ultra-low-speed die casting engine support bracket was conducted, and effects of different injection speed, the thickness of ingate, pouring temperature of liquid metal, the mould structure and the control methods of the mould temperature on the quality of die casting support bracket were discussed. The results show that the support bracket exhibits acceptable quality with low injection speed of 0. 25 m/s and high injection speed of 0. 5 m/s, thickness of ingate of 5. 2 mm as well as pouring temperature of 680~690 ℃. Through modifying die casting die structure and adopting the sequential solidification mould temperature, the support bracket ca be treated by T6 heat treatment, improving greatly the performance of the die castings.

  9. Rescaling of the Roe scheme in low Mach-number flow regions

    Science.gov (United States)

    Boniface, Jean-Christophe

    2017-01-01

    A rescaled matrix-valued dissipation is reformulated for the Roe scheme in low Mach-number flow regions from a well known family of local low-speed preconditioners popularized by Turkel. The rescaling is obtained explicitly by suppressing the pre-multiplication of the preconditioner with the time derivative and by deriving the full set of eigenspaces of the Roe-Turkel matrix dissipation. This formulation preserves the time consistency and does not require to reformulate the boundary conditions based on the characteristic theory. The dissipation matrix achieves by construction the proper scaling in low-speed flow regions and returns the original Roe scheme at the sonic line. We find that all eigenvalues are nonnegative in the subsonic regime. However, it becomes necessary to formulate a stringent stability condition to the explicit scheme in the low-speed flow regions based on the spectral radius of the rescaled matrix dissipation. With the large disparity of the eigenvalues in the dissipation matrix, this formulation raises a two-timescale problem for the acoustic waves, which is circumvented for a steady-state iterative procedure by the development of a robust implicit characteristic matrix time-stepping scheme. The behaviour of the modified eigenvalues in the incompressible limit and at the sonic line also suggests applying the entropy correction carefully, especially for complex non-linear flows.

  10. Numerical Simulation of Multi-Stage Turbomachinery Flows

    Science.gov (United States)

    Adamczyk, John J.; Hathaway, Michael D.; Shabbir, Aamir; Wellborn, Steven R.

    1999-01-01

    A comprehensive assessment is made of the predictive capability of the average passage flow model as applied to multi-stage axial flow compressors. The average passage flow model describes the time average flow field within a typical passage of a blade row embedded in a multi-stage configuration. In this work data taken within a four and one-half stage large low speed compressor will be used to assess the weakness and strengths of the predictive capabilities of the average passage flow model. The low speed compressor blading is of modern design and employs stators with end-bends. Measurements were made with slow and high response instrumentation. The high response measurements revealed the velocity components of both the rotor and stator wakes. Based on the measured wake profiles it will be argued that blade boundary layer transition is playing an important role in setting compressor performance. A model which mimics the effects of blade boundary layer transition within the frame work of the average passage model will be presented. Simulations which incorporated this model showed a dramatic improvement in agreement with data.

  11. Performance studies on an axial flow compressor stage

    Science.gov (United States)

    Sitaram, N.

    1986-12-01

    A low-speed, medium loaded axial flow compressor stage is studied experimentally and theoretically. The flow compressor facility, composed of an inlet guide vane row, a rotor blade row, and a stator blade row, and the principles of the streamline curvature method (SCM) and the Douglas-Neumann cascade program are described. The radial distribution of the flow properties, the rotor blade static pressure distribution, and the lift coefficient and relative flow angle derived experimentally and theoretically are compared. It is determined that there is good correlation between the experimental flow properties and the SCM data, the Douglas-Neumann cascade program and experimental rotor blade static pressure data, and the experimental and theoretical lift coefficients only in the midspan region. Modifications to the SCM and the Douglas-Neumann cascade program in order to improve their accuracy are discussed.

  12. Coronary Artery Stenosis Flow: Experimental and Computational Investigation

    Science.gov (United States)

    Egelhoff, Carla; Budwig, Ralph; Hansen, Byron; Foster, Jonathan

    2000-11-01

    The effects of symmetry, flowrate, wall roughness and size are investigated using realistic pulsatile waveforms for flow viz and LDV experimental models as well as CFD models using original code. Distal to the stenosis flow is characterized by a high speed jet which is central for symmetric models and attached to the wall for eccentric models. The jet is accompanied by a low speed recirculation zone which persists while lengthening and shortening during most of the cardiac cycle. Of particular note is the downstream onset of flow instability and turbulence for high flow rate conditions in symmetric and eccentric severely occluded stenoses. The location and extent of the unstable flow region continually changes throughout the cycle, which may be a factor contributing to the thrombogenesis which coronary arteries experience.

  13. Numerical simulation of two-phase turbulent flow in hydraulic and hydropower engineering

    Institute of Scientific and Technical Information of China (English)

    2007-01-01

    In connection with the specific features of high velocity aerated flow generated by hydraulic engineering structures,the mathematical model is developed for high turbulence air-water two-phase flow with the use of twin flow theoretical model in this paper.Furthermore the numerical method is proposed to treat bubbled flows.In addition,on the basis of air-water stratified twin flow model,the new calculation methods and free surface tracking technique are proposed to describe complicated movements of the free surface.Finally,the proposed model is used to calculate artificial aerated flows.The computed results coincide quite well with experimental results.This means that the proposed method can provide solid basis for practical engineering design.

  14. Improved 2D Intelligent Driver Model simulating synchronized flow and evolution concavity in traffic flow

    CERN Document Server

    Tian, Junfang; Li, Geng; Treiber, Martin; Zhu, Chenqiang; Jia, Bin

    2016-01-01

    This paper firstly show that 2 Dimensional Intelligent Driver Model (Jiang et al., PloS one, 9(4), e94351, 2014) is not able to replicate the synchronized traffic flow. Then we propose an improved model by considering the difference between the driving behaviors at high speeds and that at low speeds. Simulations show that the improved model can reproduce the phase transition from synchronized flow to wide moving jams, the spatiotemporal patterns of traffic flow induced by traffic bottleneck, and the evolution concavity of traffic oscillations (i.e. the standard deviation of the velocities of vehicles increases in a concave/linear way along the platoon). Validating results show that the empirical time series of traffic speed obtained from Floating Car Data can be well simulated as well.

  15. Generalized second-order slip boundary condition for nonequilibrium gas flows

    Science.gov (United States)

    Guo, Zhaoli; Qin, Jishun; Zheng, Chuguang

    2014-01-01

    It is a challenging task to model nonequilibrium gas flows within a continuum-fluid framework. Recently some extended hydrodynamic models in the Navier-Stokes formulation have been developed for such flows. A key problem in the application of such models is that suitable boundary conditions must be specified. In the present work, a generalized second-order slip boundary condition is developed in which an effective mean-free path considering the wall effect is used. By combining this slip scheme with certain extended Navier-Stokes constitutive relation models, we obtained a method for nonequilibrium gas flows with solid boundaries. The method is applied to several rarefied gas flows involving planar or curved walls, including the Kramers' problem, the planar Poiseuille flow, the cylindrical Couette flow, and the low speed flow over a sphere. The results show that the proposed method is able to give satisfied predictions, indicating the good potential of the method for nonequilibrium flows.

  16. Device for Measuring Low Flow Speed in a Duct

    Science.gov (United States)

    Quinn, Frank; Magee, Kevin

    2009-01-01

    A multiple-throat venturi system has been invented for measuring laminar flow of air or other gas at low speed (1 to 30 cm/s) in a duct while preserving the laminar nature of the flow and keeping the velocity profile across the duct as nearly flat as possible. While means for measuring flows at higher speeds are well established, heretofore, there have been no reliable means for making consistent, accurate measurements in this speed range. In the original application for which this system was invented, the duct leads into the test section of a low-speed wind tunnel wherein uniform, low-speed, laminar flow is required for scientific experiments. The system could also be used to monitor a slow flow of gas in an industrial process like chemical vapor deposition. In the original application, the multiple- throat venturi system is mounted at the inlet end of the duct having a rectangular cross section of 19 by 14 cm, just upstream of an assembly of inlet screens and flow straighteners that help to suppress undesired flow fluctuations (see Figure 1). The basic venturi measurement principle is well established: One measures the difference in pressure between (1) a point just outside the inlet, where the pressure is highest and the kinetic energy lowest; and (2) the narrowest part (the throat) of the venturi passage, where the kinetic energy is highest and the pressure is lowest. Then by use of Bernoulli s equation for the relationship between pressure and kinetic energy, the volumetric flow speed in the duct can be calculated from the pressure difference and the inlet and throat widths. The design of this system represents a compromise among length, pressure recovery, uniformity of flow, and complexity of assembly. Traditionally, venturis are used to measure faster flows in narrower cross sections, with longer upstream and downstream passages to maintain accuracy. The dimensions of the passages of the present venturi system are sized to provide a readily measurable

  17. Analysis of atmospheric flow over a surface protrusion using the turbulence kinetic energy equation

    Science.gov (United States)

    Frost, W.; Harper, W. L.; Fichtl, G. H.

    1975-01-01

    Atmospheric flow fields resulting from a semi-elliptical surface obstruction in an otherwise horizontally homogeneous statistically stationary flow are modelled with the boundary-layer/Boussinesq-approximation of the governing equation of fluid mechanics. The turbulence kinetic energy equation is used to determine the dissipative effects of turbulent shear on the mean flow. Mean-flow results are compared with those given in a previous paper where the same problem was attacked using a Prandtl mixing-length hypothesis. Iso-lines of turbulence kinetic energy and turbulence intensity are plotted in the plane of the flow. They highlight regions of high turbulence intensity in the stagnation zone and sharp gradients in intensity along the transition from adverse to favourable pressure gradient.

  18. Exact near-wall traveling waves of plane Poiseuille flow

    Science.gov (United States)

    Gibson, John; Brand, Evan

    2013-11-01

    We present several spatially-localized equilibrium and traveling-wave solutions of plane Couette and plane Poiseuille flow. The solutions consist of highly concentrated and spanwise-localized alternating streamwise rolls, centered over low-speed streamwise streaks and flanked on either side by high-speed streaks. For large Reynolds numbers the solutions develop critical layers that are concentrated at isolated points on the critical surface u = c . For several traveling-wave solutions of plane Poiseuille flow, the rolls are concentrated near one wall, producing streaks near the wall and larger reduction of the bulk flow in the core. These solutions form particularly isolated and elemental versions of near-wall coherent structures in shear flows and capture, as precise time-independent solutions of Navier-Stokes, the process by which near-wall rolls exchange momentum between the wall and core regions and thereby increase drag.

  19. Real-time solution of nonlinear potential flow equations for lifting rotors

    Directory of Open Access Journals (Sweden)

    Jianzhe HUANG

    2017-06-01

    Full Text Available Analysis of rotorcraft dynamics requires solution of the rotor induced flow field. Often, the appropriate model to be used for induced flow is nonlinear potential flow theory (which is the basis of vortex-lattice methods. These nonlinear potential flow equations sometimes must be solved in real time––such as for real-time flight simulation, when observers are needed for controllers, or in preliminary design computations. In this paper, the major effects of nonlinearities on induced flow are studied for lifting rotors in low-speed flight and hover. The approach is to use a nonlinear state-space model of the induced flow based on a Galerkin treatment of the potential flow equations.

  20. New exact coherent states in plane Poiseuille flow

    Science.gov (United States)

    Nagata, Masato; Deguchi, Kengo

    2012-11-01

    Two new classes of traveling wave solution are found in plane Poiseuille flow by continuing the stationary and traveling hairpin vortex states in plane Couette flow. One of them, referred to as MS hereafter, arises from a saddle-node bifurcation, characterized by two planes of mirror-symmetry perpendicular to the span-wise direction. The second new class solution, referred to as AS hereafter, bifurcates by breaking the mid-plane symmetry of the first class. Both MS and AS are characterized by two quasi-stream-wise low-speed streaks within one span-wise period. The low-speed streaks are aligned with the vertical planes of mirror symmetry, with their width varying in a varicose fashion in the stream-wise direction. These streaks appear close to both top and bottom channel walls for MS, and to only one of the channel walls for AS. We find that the Reynolds numbers at the saddle-node bifurcation for MS and AS are smaller than that of the exact coherent state in plane Poiseuille flow known to date found by Waleffe (2003).

  1. Turbulence characteristics in skimming flows on stepped spillways

    Energy Technology Data Exchange (ETDEWEB)

    Carosi, G.; Chanson, H. [Queensland Univ., Brisbane (Australia). Div. of Civil Engineering

    2008-09-15

    Stepped spillways are used to increase the rate of energy dissipation of reinforced cement concrete (RCC) dams. Modern stepped spillways are often designed for large discharge capacities that correspond to skimming flow regimes. Skimming flows are non-aerated at the upstream end of the chute, while free-surface aeration occurs when turbulent shear next to the free surface is larger than the bubble resistance created by surface tension and buoyancy. This study investigated the air-water flow properties in skimming flows related to turbulent characteristics. Experiments were conducted at a hydraulics laboratory using a broad-crested weir with a stepped chute. Measurements were conducted using phase-detection intrusive probes. Air-water flow properties were recorded for several flow rates in order to determine the distributions of turbulence intensity and integral length scales. Air-water interfacial velocities were obtained using a basic correlation analysis between the 2 sensors of a double-tip probe. Turbulence levels were derived from the relative width of a cross-correlation function. Probability distribution functions of the air bubbles and water droplet chords were analyzed in terms of bubble chords in the bubbly flow. The study demonstrated that some turbulent energy was dissipated in the form of large vortices in the bull of the flow, while the stepped cavities contributed to turbulence production. It was concluded that the rate of energy dissipation on stepped spillways is related to high turbulence levels and large-scale vortical structures. 43 refs., 3 tabs., 9 figs.

  2. Experimental study of a co-flowing jet in ONERA’s F2 research wind tunnel by 3D background oriented schlieren

    Science.gov (United States)

    Nicolas, F.; Donjat, D.; Plyer, A.; Champagnat, F.; Le Besnerais, G.; Micheli, F.; Cornic, P.; Le Sant, Y.; Deluc, J. M.

    2017-08-01

    This paper describes the first application of 3D density reconstruction from a limited number of background oriented schlieren (BOS) images in a large research-type low speed wind tunnel. The tested flow is an ad hoc co-flowing hot jet generated at the wingtip of a simplified airfoil. Ray deviation maps captured by 12 synchronized cameras are combined to reconstruct the three dimensional density field of the jet, in the line of the direct 3D BOS technique described in Nicolas et al (2016 Exp. Fluids 57 1-21). A comparison with thermocouple sampling shows consistent results and highlights the efficiency of this new method for thermal measurement of a low speed convective flow. Finally, we underline the new possibilities for fluid dynamic characterization offered by combining stereo particle image velocimetry and 3D BOS measurements.

  3. Performance of 15-Stage Experimental J71 Axial-Flow Compressor. III - Effects of Inlet-Guide-Vane Adjustment

    Science.gov (United States)

    Lucas, James G.; Filippi, Richard E.

    1955-01-01

    The stall-limit line at low speeds was improved somewhat by closing the inlet guide vanes 6 deg, while the design-speed maximum flow and pressure ratio were reduced. The first-stage characteristic curve was moved to lower values of both flog coefficient and equivalent pressure ratio. The second-stage pressure ratio was decreased slightly at high speeds, while the later stages were unaffected.

  4. Flow visualisation of the external flow from a converging slot-hole film-cooling geometry

    Science.gov (United States)

    Sargison, J. E.; Oldfield, M. L. G.; Guo, S. M.; Lock, G. D.; Rawlinson, A. J.

    2005-03-01

    This paper presents flow visualisation experiments for a novel film-cooling hole, the converging slot-hole or console for short. Previously published experimental results have demonstrated that the console improved both the heat transfer and the aerodynamic performance of turbine vane and rotor blade cooling systems. Flow visualisation data for a row of consoles were compared with that of cylindrical and fan-shaped holes and a slot at the same inclination angle of 35° to the surface, on a large-scale, flat-plate model at engine-representative Reynolds numbers in a low speed tunnel with ambient temperature mainstream flow. In the first set of experiments, the flow was visualised by using a fine nylon mesh covered with thermochromic liquid crystals, allowing the measurement of gas temperature contours in planes perpendicular to the flow. This data demonstrated that the console film was similar to a slot film, and remained thin and attached to the surface for the coolant-to-mainstream momentum flux ratios of 1.1 to 40 and for a case with no crossflow (infinite momentum flux ratio). A second set of flow visualisation experiments using water/dry-ice fog have confirmed these results and have shown that the flow through all coolant geometries is unsteady.

  5. Simulation of fluid flow inside a continuous slab-casting machine

    Science.gov (United States)

    Thomas, B. G.; Mika, L. J.; Najjar, F. M.

    1990-04-01

    A finite element model has been developed and applied to compute the fluid flow distribution inside the shell in the mold region of a continuous, steel slab-casting machine. The model was produced with the commercial program FIDAP, which allows this nonlinear, highly turbulent problem to be simulated using the K- ɛ turbulence model. It consists of separate two-dimensional (2-D) models of the nozzle and a section through the mold, facing the broad face. The predicted flow patterns and velocity fields show reasonable agreement with experimental observations and measurements conducted using a transparent plastic water model. The effects of nozzle angle, casting speed, mold width, and turbulence simulation parameters on the flow pattern have been investigated. The overall flow field is relatively insensitive to process parameters.

  6. A hot-wire method for high-intensity turbulent flows

    Science.gov (United States)

    Mueller, U. R.

    1983-01-01

    A measuring technique for determing instantaneous, three-dimensional velocity vectors in highly turbulent flows by means of a 4-sensor hot-wire probe is described. As is well known, the hot-wire signal received in reversing flows cannot uniquely be interpreted. This difficulty is circumvented by tracking the thermal wake of a heated wire. Whenever the approximate flow direction is indicated by a temperature-sensitive wake detector, all components of the instantaneous velocity vector are evaluated by means of a digital data reduction method. Uniqueness of the solution derived from the triple-hot-wire response equations is examined. A first application of the proposed measuring technique in the recirculating flow downstream of a backward-facing step is described.

  7. Turbulent structures in wall-bounded shear flows observed via three-dimensional numerical simulators. [using the Illiac 4 computer

    Science.gov (United States)

    Leonard, A.

    1980-01-01

    Three recent simulations of tubulent shear flow bounded by a wall using the Illiac computer are reported. These are: (1) vibrating-ribbon experiments; (2) study of the evolution of a spot-like disturbance in a laminar boundary layer; and (3) investigation of turbulent channel flow. A number of persistent flow structures were observed, including streamwise and vertical vorticity distributions near the wall, low-speed and high-speed streaks, and local regions of intense vertical velocity. The role of these structures in, for example, the growth or maintenance of turbulence is discussed. The problem of representing the large range of turbulent scales in a computer simulation is also discussed.

  8. Bi-stability in turbulent, rotating spherical Couette flow

    CERN Document Server

    Zimmerman, Daniel S; Lathrop, Daniel P; 10.1063/1.3593465

    2011-01-01

    Flow between concentric spheres of radius ratio $\\eta = r_\\mathrm{i}/r_\\mathrm{o} = 0.35$ is studied in a 3 m outer diameter experiment. We have measured the torques required to maintain constant boundary speeds as well as localized wall shear stress, velocity, and pressure. At low Ekman number $E = 2.1\\times10^{-7}$ and modest Rossby number $0.07 < Ro < 3.4$, the resulting flow is highly turbulent, with a Reynolds number ($Re=Ro/E$) exceeding fifteen million. Several turbulent flow regimes are evident as $Ro$ is varied for fixed $E$. We focus our attention on one flow transition in particular, between $Ro = 1.8$ and $Ro = 2.6$, where the flow shows bistable behavior. For $Ro$ within this range, the flow undergoes intermittent transitions between the states observed alone at adjacent $Ro$ outside the switching range. The two states are clearly distinguished in all measured flow quantities, including a striking reduction in torque demanded from the inner sphere by the state lying at higher $Ro$. The redu...

  9. Experimental Study of Tip Vortex Flow from a Periodically Pitched Airfoil Section

    Science.gov (United States)

    Zaman, Khairul; Fagan, Amy; Mankbadi, Mina

    2016-01-01

    An experimental investigation of tip vortex flow from a NACA0012 airfoil, pitched periodically at various frequencies, is conducted in a low-speed wind tunnel. Initially, data for stationary airfoil held fixed at various angles-of-attack are gathered. Flow visualization pictures as well as detailed cross-sectional properties areobtained at various streamwise locations using hot-wire anemometry. Data include mean velocity, streamwise vorticity as well as various turbulent stresses. Preliminary data are also acquired for periodically pitched airfoil. These results are briefly presented in this extended abstract.

  10. Breakdown parameter for kinetic modeling of multiscale gas flows.

    Science.gov (United States)

    Meng, Jianping; Dongari, Nishanth; Reese, Jason M; Zhang, Yonghao

    2014-06-01

    Multiscale methods built purely on the kinetic theory of gases provide information about the molecular velocity distribution function. It is therefore both important and feasible to establish new breakdown parameters for assessing the appropriateness of a fluid description at the continuum level by utilizing kinetic information rather than macroscopic flow quantities alone. We propose a new kinetic criterion to indirectly assess the errors introduced by a continuum-level description of the gas flow. The analysis, which includes numerical demonstrations, focuses on the validity of the Navier-Stokes-Fourier equations and corresponding kinetic models and reveals that the new criterion can consistently indicate the validity of continuum-level modeling in both low-speed and high-speed flows at different Knudsen numbers.

  11. An experimental study of the flow in a wing with a partial span drooped leading edge

    Science.gov (United States)

    Winkelmann, A. E.; Tsao, C. P.

    1981-01-01

    The flow field produced by a low aspect ratio wing (AR = 3.0) with a partial span leading edge droop was investigated in a series of low speed wind tunnel tests (Reynolds number based on 17.8 cm chord = 560,000). Photographs were obtained of surface oil flow patterns over an angle of attack range of alpha = 0 to 29 deg. Flow field surveys of the partially stalled wing at alpha = 25 deg were completed using a hot-wire probe, a split-film probe and a Conrad probe. The flow field survey data was presented using a color video display. The data indicated regions of apparent reversed flow in the separation region behind the wing and indicated the general cross-sectional shape of the separated wake flow.

  12. Analysis of atmospheric flow over a surface protrusion using the turbulence kinetic energy equation with reference to aeronautical operating systems

    Science.gov (United States)

    Frost, W.; Harper, W. L.

    1975-01-01

    Flow over surface obstructions can produce significantly large wind shears such that adverse flying conditions can occur for aeronautical systems (helicopters, STOL vehicles, etc.). Atmospheric flow fields resulting from a semi-elliptical surface obstruction in an otherwise horizontally homogeneous statistically stationary flow are modelled with the boundary-layer/Boussinesq-approximation of the governing equation of fluid mechanics. The turbulence kinetic energy equation is used to determine the dissipative effects of turbulent shear on the mean flow. Iso-lines of turbulence kinetic energy and turbulence intensity are plotted in the plane of the flow and highlight regions of high turbulence intensity in the stagnation zone and sharp gradients in intensity along the transition from adverse to favourable pressure gradient. Discussion of the effects of the disturbed wind field in CTOL and STOL aircraft flight path and obstruction clearance standards is given. The results indicate that closer inspection of these presently recommended standards as influenced by wind over irregular terrains is required.

  13. Experimental and numerical investigations of three-dimensional turbulent flow of water surrounding a CANDU simulation fuel bundle structure inside a channel

    Energy Technology Data Exchange (ETDEWEB)

    Abbasian, F.; Yu, S.D. [Department of Mechanical and Industrial Engineering, Ryerson University, 350 Victoria Street, Toronto, Ontario, M5B 2K3 (Canada); Cao, J. [Department of Mechanical and Industrial Engineering, Ryerson University, 350 Victoria Street, Toronto, Ontario, M5B 2K3 (Canada)], E-mail: jcao@ryerson.ca

    2009-11-15

    Computational fluid dynamics (CFD) is used to simulate highly turbulent coolant flows surrounding a simulation CANDU fuel bundle structure inside a flow channel. Three CFD methods are used: large eddy simulation (LES), detached eddy simulation (DES), and Reynolds stress model (RSM). The outcome of the simulations is compared with the experimental pressure data measured using an in-water microphone and a miniature pressure transducer placed at various locations in the vicinity of the bundle structure. Among all the three methods employed in developing computational models, LES provides the most accurate results for turbulent pressures.

  14. Low-speed aerodynamic performance of a high-aspect-ratio supercritical-wing transport model equipped with full-span slat and part-span double-slotted flaps

    Science.gov (United States)

    Morgan, H. L., Jr.; Paulson, J. W., Jr.

    1979-01-01

    An investigation was conducted in the Langley V/STOL tunnel to determine the static longitudinal and lateral-directional aerodynamic characteristics of an advanced high-aspect-ratio supercritical-wing transport model equipped with a full-span leading-edge slat and part-span double-slotted trailing-edge flaps. This wide-body transport model was also equipped with spoiler and aileron control surfaces, flow-through nacelles, landing gear, movable horizontal tails, and interchangeable wing tips with aspect ratios of 10 and 12. The model was tested with leading-edge slat and trailing-edge flap combinations representative of cruise, climb, takeoff, and landing wing configurations. The tests were conducted at free-stream conditions corresponding to Reynolds numbers (based on mean geometric chord) of 0.97 to 1.63 x 10 to the 6th power and corresponding Mach numbers of 0.12 to 0.20, through an angle-of-attack range of -2 deg to 24 deg and a sideslip-angle range of -10 deg to 5 deg.

  15. Flow structure around high-speed train in open air

    Institute of Scientific and Technical Information of China (English)

    田红旗; 黄莎; 杨明智

    2015-01-01

    According to the analysis of the turbulent intensity level around the high-speed train, the maximum turbulent intensity ranges from 0.2 to 0.5 which belongs to high turbulent flow. The flow field distribution law was studied and eight types of flow regions were proposed. They are high pressure with air stagnant region, pressure decreasing with air accelerating region, low pressure with high air flow velocity region I, turbulent region, steady flow region, low pressure with high air flow velocity region II, pressure increasing with air decelerating region and wake region. The analysis of the vortex structure around the train shows that the vortex is mainly induced by structures with complex mutation and large curvature change. The head and rear of train, the underbody structure, the carriage connection section and the wake region are the main vortex generating sources while the train body with even cross-section has rare vortexes. The wake structure development law studied lays foundation for the train drag reduction.

  16. A Study on the Uncertainty of Flow-Induced Vibration in a Cross Flow over Staggered Tubes

    Energy Technology Data Exchange (ETDEWEB)

    Kim, Ji-Su; Park, Jong-Woon [Dongguk univ, Gyeong Ju (Korea, Republic of); Choi, Hyeon-Kyeong [HanNam University, Daejeon (Korea, Republic of)

    2015-05-15

    Cross-flow in many support columns of very high temperature reactor (VHTR) lower plenum would have FIV issues under high speed flow jetting from the core. For a group of multiple circular cylinders subjected to a cross-flow, three types of potential vibration mechanisms may exist: (1) Vortex-induced vibration (VIV), (2) Fluid-elastic vibration (FEV) and (3) Turbulence-induced vibration (TIV). Kevalahan studied the free vibration of circular cylinders in a tightly packed periodic square inline array of cylinders. Pandey et al. studied the flue gas flow distribution in the Low Temperature Super Heater (LTSH) tube bundles situated in second pass of a utility boiler and the phenomenon of flow induced vibration. Nakamura et al. studied flow instability of cylinder arrays resembling U-bend tubes in steam generators. The FIV evaluation is usually performed with computational fluid dynamic (CFD) analysis to obtain unknown frequency of oscillation of the multiple objects under turbulent flow and thus the uncertainty residing in the turbulence model used should be quantified. In this paper, potential FIV uncertainty arising from the turbulence phenomena are evaluated for a typical cross flow through staggered tube bundles resembling the VHTR lower plenum support columns. Flow induced vibration (FIV) is one of the important mechanical and fatigue issues in nuclear systems. Especially, cross-flow in many support structures of VHTR lower plenum would have FIV issues under highly turbulent jet flows from the core. The results show that the effect of turbulence parameters on FIV is not negligible and the uncertainty is 5 to 10%. Present method can be applied to future FIV evaluations of nuclear systems. More extensive studies on flow induced vibration in a plant scale by using more rigorous computational methods are under way.

  17. Characteristics of sheath-driven tangential flow produced by a low-current DC surface glow discharge plasma actuator

    Science.gov (United States)

    Shin, Jichul; Shajid Rahman, Mohammad

    2014-08-01

    An experimental investigation of low-speed flow actuation at near-atmospheric pressure is presented. The flow actuation is achieved via low-current ( \\lesssim 1.0 mA) continuous or pulsed DC surface glow discharge plasma. The plasma actuator, consisting of two sharp-edged nickel electrodes, produces a tangential flow in a direction from anode to cathode, and is visualized using high-speed schlieren photography. The induced flow velocity estimated via the schlieren images reaches up to 5 m/s in test cases. The actuation capability increases with pressure and electrode gap distances, and the induced flow velocity increases logarithmically with the discharge power. Pulsed DC exhibits slightly improved actuation capability with better directionality. An analytic estimation of induced flow velocity obtained based on ion momentum in the cathode sheath and gas dynamics in one-dimensional flow yields values similar to those measured.

  18. Kinematic dynamo simulations of von K\\'arm\\'an flows: application to the VKS experiment

    CERN Document Server

    Pinter, A; Daviaud, F; Leorat, J

    2011-01-01

    The VKS experiment has evidenced dynamo action in a highly turbulent liquid sodium von K\\'arm\\'an flow [R. Monchaux et al., Phys. Rev. Lett. {\\bf 98}, 044502 (2007)]. However, the existence and the onset of a dynamo happen to depend on the exact experimental configuration. By performing kinematic dynamo simulations on real flows, we study their influence on dynamo action, in particular the sense of rotation and the presence of an annulus in the shear layer plane. The 3 components of the mean velocity fields are measured in a water prototype for different VKS configurations through Stereoscopic Particle Imaging Velocimetry. Experimental data are then processed in order to use them in a periodic cylindrical kinematic code. Even if the kinematic predicted mode appears to be different from the experimental saturated one, the results concerning the existence of a dynamo and the thresholds are in qualitative agreement, showing the importance of the flow characteristics.

  19. Calculation of compressible boundary layer flow about airfoils by a finite element/finite difference method

    Science.gov (United States)

    Strong, Stuart L.; Meade, Andrew J., Jr.

    1992-01-01

    Preliminary results are presented of a finite element/finite difference method (semidiscrete Galerkin method) used to calculate compressible boundary layer flow about airfoils, in which the group finite element scheme is applied to the Dorodnitsyn formulation of the boundary layer equations. The semidiscrete Galerkin (SDG) method promises to be fast, accurate and computationally efficient. The SDG method can also be applied to any smoothly connected airfoil shape without modification and possesses the potential capability of calculating boundary layer solutions beyond flow separation. Results are presented for low speed laminar flow past a circular cylinder and past a NACA 0012 airfoil at zero angle of attack at a Mach number of 0.5. Also shown are results for compressible flow past a flat plate for a Mach number range of 0 to 10 and results for incompressible turbulent flow past a flat plate. All numerical solutions assume an attached boundary layer.

  20. Efficiency of energy separation at compressible gas flow in a planar duct

    Science.gov (United States)

    Makarov, M. S.; Makarova, S. N.

    2014-12-01

    The method of energy separation in a high-speed flow proposed by A.I. Leontyev is investigated numerically. The adiabatic compressible gas flow (of a helium-xenon mixture) with a low Prandtl number in a planar narrow duct and a flow with heat exchange in a duct partitioned by a heat-conducting wall are analysed. The temperature recovery factor on the adiabatic wall, degree of cooling the low-speed flow part, temperature efficiency, and the adiabatic efficiency in a duct with heat exchange are estimated. The data are obtained for the first time, which make it possible to compare the efficiency of energy separation in a high-speed flow with the efficiency of similar processes in vortex tubes and other setups of gas-dynamic energy separation.

  1. Comparison of Simultaneous PIV and Hydroxyl Tagging Velocimetry in Low Velocity Flows

    Science.gov (United States)

    Andre, Matthieu A.; Bardet, Philippe M.; Burns, Ross A.; Danehy, Paul M.

    2016-01-01

    Hydroxyl tagging velocimetry (HTV) is a molecular tagging velocimetry (MTV) technique that relies on the photo- dissociation of water vapor into OH radicals and their subsequent tracking using laser-induced fluorescence. At ambient temperature in air, the OH species lifetime is about 50 micro-s. The feasibility of using HTV for probing low- speed flows (a few m/s) is investigated by using an inert, heated gas as a means to increase the OH species lifetime. Unlike particle-based techniques, MTV does not suffer from tracer settling, which is particularly problematic at low speeds. Furthermore, the flow needs to be seeded with only a small mole fraction of water vapor, making it safer for both the user and facilities than other MTV techniques based on corrosive or toxic chemical tracers. HTV is demonstrated on a steam-seeded nitrogen jet at approximately 75 C in the laminar (Umean=3.31 m/s, Re=1,540), transitional (Umean=4.48 m/s, Re=2,039), and turbulent (Umean=6.91 m/s, Re=3,016) regimes at atmospheric pressure. The measured velocity profiles are compared with particle image velocimetry (PIV) measurements performed simultaneously with a second imager. Seeding for the PIV is achieved by introducing micron-sized water droplets into the flow with the steam; the same laser sheet is used for PIV and HTV to guarantee spatial and temporal overlap of the data. Optimizing each of these methods, however, requires conflicting operating conditions: higher temperatures benefit the HTV signals but reduce the available seed density for the PIV through evaporation. Nevertheless, data are found to agree within 10% for the instantaneous velocity profiles and within 5% for the mean profiles and demonstrate the feasibility of HTV for low-speed flows at moderate to high temperatures.

  2. Numerical analysis for supersonic turbulent mixing layers of different species gases. lst report. ; Mixing characteristics of uniform flows. Choonsoku ishu gas ranryu kongoso no suchi kaiseki. 1. ; Ichiyoryu no kongo tokusei

    Energy Technology Data Exchange (ETDEWEB)

    Nakano, S.; Ikegawa, M. (Hitachi Ltd., Tokyo (Japan))

    1990-07-25

    Flow field in which two supersonic turbulent flows with different species gases mix, was analyzed with a two-equation turbulence model and the mixing characteristics of 2 supersonic parallel flows were investigated by making the inlet flow condition of high speed gas constant and by ststematically changing the inlet flow condition of low speed gas. When mixing is carried out so that high speed gas is taken in the low speed gas, high spreading rate of the mixing layer is obtained and this tendency is emphasized markedly as the ratio such as velocity, density and pressure between low and high speed gases become small. The spreading of low mass ratio layer of low speed gas and that of low mass ratio layer of high speed gas are assymmetric and the spreading of the former is suppressed at the coindition where the latter expands. The tendency of developing rate of mixing layer to the correlating parameter in this calculation agreed well with results of visualized experiment. 14 refs., 10 figs., 3 tabs.

  3. LDA/PIV measurements of gas flow in a 4-stroke motored engine

    Energy Technology Data Exchange (ETDEWEB)

    Obokata, T.; Kato, M.; Ishima, T. [Gunma Univ., Tenjin, Kiryu (Japan). Graduate School of Mechanical Engineering; Kaneko, M. [Fuji Heavy Industries Ltd., Tokyo (Japan)

    2009-07-01

    The key technology for improving the internal combustion engine involves understanding and controlling the gas flows in the cylinder. However, it is not easy to understand the turbulence characteristics of gas flows because they are intermittent, highly turbulent, and three-dimensional complex flows. Numerical simulations of gas flow and combustion are important and powerful tools to understand the gas flows in the cylinder. It is important to verify the numerical simulation results by the reliable and detailed experimental data obtained at the same engine. This presentation discussed an investigation on the turbulent characteristics of in-cylinder flows at the same engine by laser doppler anemometry (LDA) and particulate image velocimetry for verifying the numerical results. Turbulent characteristics of gas flow in the internal combustion engine were also experimentally analysed under various operating conditions. The experimental setup was illustrated and the specifications of LDA and the test engine were identified. The prototype tumble generation valve was also illustrated and the results of the measurement of flow velocity through an intake valve and measurement of in-cylinder flow velocity were offered. Animations of the flow velocity through a valve were also presented. It was concluded that the effect of the turbulence generating valve (TGV) was clarified by the experimental data. The effect of the TGV was remarkable in the upper side of the cylinder. tabs., figs.

  4. A Theory of Unstaggered Airfoil Cascades in Compressible Flow

    Science.gov (United States)

    Spurr, Robert A.; Allen, H. Julian

    1947-01-01

    By use of the methods of thin airfoil theory, which include effects of compressibility, rela.tio^as are developed which permit the rapid determination of the pressure distribution over an unstaggered cascade of airfoils of a given profile, and the determination of the profile shape necessary to yield a given pressure distribution for small chord gap ratios, For incompressible flow the results of the theory are compared with available examples obtained by the more exact method of conformal transformation. Although the theory is developed for small chord/gap ratios, these comparisons show that it may be extended to chord/gap ratios of order unity, at least for low speed flows. Choking of cascades, a phenomenon of particular importance in compressor design, is considered.

  5. Experimental investigation of unsteady fan flow interaction with downstream struts

    Science.gov (United States)

    Ng, W. F.; Obrien, W. F.; Olsen, T. L.

    1986-07-01

    In the present study of the unsteady pressure field produced on fan rotor blades by interaction with downstream struts, a single stage, low speed axial-flow fan was instrumented with blade-mounted high frequency pressure transducers. In addition, stationary pressure problems were used to map out the flowfield. Fluctuating pressure measurements are presented for blade midspan and 85-percent span on both the suction and pressure surfaces of the rotor blades at several positions of the downstream struts, and for two different flow coefficients. The strut is found to produce an effect on the unsteady pressure field on the rotor blades; this effect exceeds that due to the stator at design rotor-stator-strut spacing, but it rapidly declines as the struts are moved downstream.

  6. Interactions between butterfly scales and unsteady flows during flapping flight

    Science.gov (United States)

    Jones, Robert; Lang, Amy

    2008-11-01

    Recent research has shown that the highly flexible wings of butterflies in flapping flight develop vortices along their leading and trailing edges. Butterfly scales (approximately 100 microns) have a shingled pattern and extend into the boundary layer. These scales could play a part in controlling separation in this 3-dimensional complex flow field. Biomimetic applications of butterfly scales may aid in the development of flapping wing micro air vehicles. In this study, we observed that the orientation of the scales may relate to the local flow field, and might move or shift during flight. Monarch butterflies were trained to fly in a low speed smoke tunnel for visualization. Scales were removed from the leading and trailing edges and specimens were photographed at 500 frames per second. Variation in flapping pattern and flight fitness are discussed.

  7. Compressive Sensing Based Machine Learning Strategy For Characterizing The Flow Around A Cylinder With Limited Pressure Measurements

    Energy Technology Data Exchange (ETDEWEB)

    Bright, Ido; Lin, Guang; Kutz, Nathan

    2013-12-05

    Compressive sensing is used to determine the flow characteristics around a cylinder (Reynolds number and pressure/flow field) from a sparse number of pressure measurements on the cylinder. Using a supervised machine learning strategy, library elements encoding the dimensionally reduced dynamics are computed for various Reynolds numbers. Convex L1 optimization is then used with a limited number of pressure measurements on the cylinder to reconstruct, or decode, the full pressure field and the resulting flow field around the cylinder. Aside from the highly turbulent regime (large Reynolds number) where only the Reynolds number can be identified, accurate reconstruction of the pressure field and Reynolds number is achieved. The proposed data-driven strategy thus achieves encoding of the fluid dynamics using the L2 norm, and robust decoding (flow field reconstruction) using the sparsity promoting L1 norm.

  8. Flow and Performance Calculations of Axial Compressor near Stall Margin

    Science.gov (United States)

    Hwang, Yoojun; Kang, Shin-Hyoung

    2010-06-01

    Three-dimensional flows through a Low Speed Research Axial Compressor were numerically conducted in order to estimate the performance through unsteady and steady-state simulations. The first stage with the inlet guide vane was investigated at the design point to confirm that the rotor blade induced periodicity exists. Special attention was paid to the flow near the stall condition to inspect the flow behavior in the vicinity of the stall margin. The performance predicted under the steady-state assumption is in good agreement with the measured data. However, the steady-state calculations induce more blockage through the blade passage. Flow separations on the blade surface and end-walls are reduced when unsteady simulation is conducted. The negative jet due to the wake of the rotor blade periodically distorts the boundary layer on the surface of the stator blade and improves the performance of the compressor in terms of the pressure rise. The advantage of the unsteadiness increases as the flow rate reduces. In addition, the rotor tip leakage flow is forced downstream by the unsteadiness. Consequently, the behavior contributes to extending the range of operation by preventing the leakage flow from proceeding upstream near the stall margin.

  9. Flow Characteristics at the Pump-Turbine Interface of a Torque Converter at Extreme Speed Ratios

    Directory of Open Access Journals (Sweden)

    A. Habsieger

    2003-01-01

    Full Text Available The average velocity field at the pump–turbine interface in a scaled version of a truck torque converter was studied. Seven different turbine-to-pump rotational-speed ratios were examined, ranging from near stall (0.065 to overspeed (1.050 so as to determine the effect of the speed ratio on the flow field and on the mass flow rate. Laser velocimetry was used to measure the flow velocity through the pump's exit and the turbine's inlet plane. At the pump's exit, as the speed ratio increases, the high velocities move to the pressure-shell corner and then to both the core-suction and the pressureshell corners. Concentrated velocity gradients are largest at the lowest speed ratio, but areas of velocity gradients are largest near the coupling point. Near the coupling point, the flow field is most nonuniform, which yields a highly periodic flow into the turbine inlet. Above the coupling point, the high velocity remains in the pressure-shell corner but separation is seen to develop at the highest speed ratio. At the turbine's inlet, reverse flow is seen at low speed ratios and is an indicator of flow leakage through the core. Velocity gradients are very large at low speed ratios. As the speed ratio increases to the coupling point, the high velocities remain on the shell side. Above the coupling point, the high-velocity flow migrates from the shell side to the core side. The mass flow rate decreases significantly and nonlinearly with the increase of the speed ratio, but for speed ratios greater than 1.000, the negative slope decreases.

  10. The high Reynolds number flow through an axial-flow pump

    Science.gov (United States)

    Zierke, W. C.; Straka, W. A.; Taylor, P. D.

    1993-11-01

    The high Reynolds number pump (HIREP) facility at ARL Penn State has been used to perform a low-speed, large-scale experiment of the incompressible flow of water through a two-blade-row turbomachine. HIREP can involve blade chord Reynolds numbers as high as 6,000,000 and can accommodate a variety of instrumentation in both a stationary and a rotating frame of reference. The objectives of this experiment were as follows: to provide a database for comparison with three-dimensional, viscous (turbulent) flow computations; to evaluate the engineering models; and to improve our physical understanding of many of the phenomena involved in this complex flow field. The experimental results include a large quantity of data acquired throughout HIREP. A five-hole probe survey of the inlet flow 37.0 percent chord upstream of the inlet guide vane (IGV) leading edge is sufficient to give information for the inflow boundary conditions, while some static-pressure information is available to help establish an outflow boundary condition.

  11. Influence of piston position on the scavenging and swirling flow in two-stoke diesel engines

    DEFF Research Database (Denmark)

    Obeidat, Anas; Haider, Sajjad; Meyer, Knud Erik

    2011-01-01

    We study the eect of piston position on the in-cylinder swirling flow in a low speed large two-stroke marine diesel engine model. We are using Large Eddy Simulations in OpenFOAM, with three different models for the turbulent flow: a one equation model (OEM), a dynamic one equation model (DOEM...... closure from a Burgers vortex profile to a solid body rotation while the axial velocity changes from a wake-like profile to a jet-like profile. The numerical results are compared with measurements in a similar geometry [3] and we find a good agreement between simulations and measurements. Furthermore, we......) and Ta Phuoc Loc's model (TPLM). The simulated flows are grid-independent and they are computed in situations analogous to two different piston positions where the air intake ports are uncovered 100% and 50%, respectively. We find that the average flow inside the cylinder changes qualitatively with port...

  12. Investigation of several passive and active methods for turbulent flow separation control

    Science.gov (United States)

    Lin, J. C.; Howard, F. G.; Bushnell, D. M.; Selby, G. V.

    1990-01-01

    Relative performance of several passive and active methods for controlling two-dimensional turbulent separated flow associated with a curved backward-facing ramp were investigated at low speeds. Surface static pressure measurement and oil flow visualization results indicate that submerged vortex generators, vortex generator jets, elongated arches at +-alpha, and large-eddy breakup devices at +-alpha placed near the baseline separation location reduce flow separation and increase pressure recovery. Spanwise cylinders reduce flow separation but decrease pressure recovery downstream. Arches with alpha = 0 deg, Helmholtz resonators, and Viets' fluidic flappers examined so far have no significant effect in reducing separation. Wall cooling computation indicates that separation delay on a partially cooled ramp is nearly the same as on a fully-cooled ramp while minimizing the frictional drag increase associated with the wall cooling process.

  13. Flow visualization

    CERN Document Server

    Merzkirch, Wolfgang

    1974-01-01

    Flow Visualization describes the most widely used methods for visualizing flows. Flow visualization evaluates certain properties of a flow field directly accessible to visual perception. Organized into five chapters, this book first presents the methods that create a visible flow pattern that could be investigated by visual inspection, such as simple dye and density-sensitive visualization methods. It then deals with the application of electron beams and streaming birefringence. Optical methods for compressible flows, hydraulic analogy, and high-speed photography are discussed in other cha

  14. On the influence of far-wake resolution on wind turbine flow simulations

    DEFF Research Database (Denmark)

    Zahle, Frederik; Sørensen, Niels N.

    2007-01-01

    resolving up to 13 tip vortex revolutions. It was found that the resolution of the tip vortices in the far-wake beyond half a diameter downstream did not influence the induced velocities in the rotor plane significantly, with the low speed shaft torque differing less than approximately 1% for the rotor......  A study was made on the influence of the wake mesh resolution on the integrated forces acting on a wind turbine rotor using an unsteady incompressible Navier-Stokes flow solver. Solutions were obtained for five wake resolutions ranging from 0.5 rotor diameters to 7.5 diameters downstream...

  15. EXPERIMENTS OF THREE-DIMENSIONAL FLOW STRUCTURE IN BRAIDED RIVERS

    Institute of Scientific and Technical Information of China (English)

    HUA Zu-lin; GU Li; CHU Ke-jian

    2009-01-01

    The braided river is a typical river pattern in nature, but there is a paucity of comprehensive data set describing the three-dimensional flow field in the braided river. A physical model experiment was used to study the flow characteristics in the typical braided river with a mid-bar between two anabranches. In the experiment, two kinds of mid-bar with the ratios of its length to maximal width of 3 and 5 were considered. Moreover, the mid-bar could be moved to adjust the width of two anabranches. The detailed measurements of velocity were conducted using an acoustic Doppler velocimeter over a grid defined throughout the whole braided river region, including the bifurcation, two anabranches and the confluence. In two kinds of mid-bar braided models, a separation zone was observed in the anabranch of the model in which the ratio of length to maximal width of mid-bar is 3, however the separation zone was not found in another model in which the ratio is 5. In addition, the opposite secondary cells were observed at the bend apex of anabranch in two models, and different longitudinal velocity distributions in the entrance region of anabranch account for this opposite flow structure. Finally, turbulent kinetic energy were shown and compared in different situations. The high turbulence occurs at the place with strong shear, especially at the boundary of the separation zone and the high velocity passing flow.

  16. Flywheels for Low-Speed Kinetic Energy Storage Systems

    Energy Technology Data Exchange (ETDEWEB)

    Portnov, G.; Cruz, I.; Arias, F.; Fiffe, R. P.

    2003-07-01

    A brief overview of different steel disc-type flywheels is presented. It contents the analysis of relationship between stress-state and kinetic energy of rotating body, comparison of the main characteristics of flywheels and description of their optimization procedures. It is shown that profiles of the discs calculated on a basis of plane stress-state assumption may be considered only as a starting point for its further improvement using 3-D approach. The aim of the review is to provide a designer for a insight into problem of shaping of steel flywheels. (Author) 19 refs.

  17. Low Speed Aerodynamics of the X-38 CRV

    Science.gov (United States)

    Komerath, N. M.; Funk, R.; Ames, R. G.; Mahalingam, R.; Matos, C.

    1998-01-01

    This project was performed in support of the engineering development of the NASA X-38 Crew Return Vehicle (CRV)system. Wind tunnel experiments were used to visualize various aerodynamic phenomena encountered by the CRV during the final stages of descent and landing. Scale models of the CRV were used to visualize vortex structures above and below the vehicle, and in its wake, and to quantify their trajectories. The effect of flaperon deflection on these structures was studied. The structure and dynamics of the CRV's wake during the drag parachute deployment stage were measured. Regions of high vorticity were identified using surveys conducted in several planes using a vortex meter. Periodic shedding of the vortex sheets from the sides of the CRV was observed using laser sheet videography as the CRV reached high angles of attack during the quasi-steady pitch-up prior to parafoil deployment. Using spectral analysis of hot-film anemometer data, the Strouhal number of these wake fluctuations was found to be 0.14 based on the model span. Phenomena encountered in flight test during parafoil operation were captured in scale-model tests, and a video photogrammetry technique was implemented to obtain parafoil surface shapes during flight in the tunnel. Forces on the parafoil were resolved using tension gages on individual lines. The temporal evolution of the phenomenon of leading edge collapse was captured. Laser velocimetry was used to demonstrate measurement of the porosity of the parafoil surface. From these measurements, several physical explanations have been developed for phenomena observed at various stages of the X-38 development program. Quantitative measurement capabilities have also been demonstrated for continued refinement of the aerodynamic technologies employed in the X-38 project. Detailed results from these studies are given in an AIAA Paper, two slide presentations, and other material which are given on a Web-based archival resource. This is the Digital Library of the Georgia Tech Experimental Aerodynamics Group.

  18. DESIGN AND FABRICATION OF A LOW SPEED IMPACT TESTER

    Directory of Open Access Journals (Sweden)

    M. Navarrete

    2004-12-01

    Full Text Available The impact response of sandwich panels with an improved structure to increase their impact resistance isinvestigated. In order to compare the impact performance of sandwich structures, a specific and instrumenteddrop-weight impact tester was designed and developed. The experimental part of this work is an evaluation oncomposite sandwich panels behavior used in the manufacturing of the UNAM Electrobús chassis. Two differentsandwich structures are analyzed: the first type is a structure composed by a glass fiber-polyester matrix compositefacesheets and a polyethylene honeycomb core. The second one consists of facesheets made from a glass fiberepoxymatrix composite laminate and core formed by internal phenolic honeycomb structure. The first structurewas specifically designed to improve crashworthiness for transport applications. The main results of this study areevaluated from the absorbed energy performance of the sandwich structures subjected to a single impact, and thedevelopment of useful criteria for materials selection.

  19. Handling Qualities of Large Rotorcraft in Hover and Low Speed

    Science.gov (United States)

    2015-03-01

    119 Appendix C—Pilot Questionnaire ...data, task performance, and pilot comments were recorded. A questionnaire (included as Appendix C) was used to elicit structured pilot opinion about...MTEs from ADS-33. Specifically, these were the Hover, Lateral Reposition, Pirouette, Hovering Turn, and Depart/ Abort MTEs. However, the majority of

  20. Noisiness of the Surfaces on Low-Speed Roads

    Directory of Open Access Journals (Sweden)

    Wladyslaw Gardziejczyk

    2016-03-01

    Full Text Available Traffic noise is a particular threat to the environment in the vicinity of roads. The level of the noise is influenced by traffic density and traffic composition, as well as vehicle speed and the type of surface. The article presents the results of studies on tire/road noise from passing vehicles at a speed of 40–80 kph, carried out by using the statistical pass-by method (SPB, on seven surfaces with different characteristics. It has been shown that increasing the speed from 40 kph to 50 kph contributes to the increase in the maximum A-weighted sound pressure level by about 3 dB, regardless of the type of surface. For larger differences in speed (30 kph–40 kph increase in noise levels reaches values about 10 dB. In the case of higher speeds, this increase is slightly lower. In this article, special attention is paid to the noisiness from surfaces made of porous asphalt concrete (PAC, BBTM (thin asphalt layer, and stone mastic asphalt (SMA with a maximum aggregate size of 8 mm and 5 mm. It has also been proved that surfaces of porous asphalt concrete, within two years after the commissioning, significantly contribute to a reduction of the maximum level of noise in the streets and roads with lower speed of passing cars. Reduction of the maximum A-weighted sound pressure level of a statistical car traveling at 60 kph reaches values of up to about 6 dB, as compared with the SMA11. Along with the exploitation of the road, air voids in the low-noise surface becomes clogged and acoustic properties of the road decrease to a level similar to standard asphalt.

  1. Velocity Measurement Systems for a Low-speed Wind Tunnel

    Science.gov (United States)

    2015-04-29

    connecting the probes to the anemometer and for manipulating their positions. Funds for additional components to complete the hot-wire system were...focus area, particularly unmanned aerial vehicles (UAVs) and remotely- operated vehicles ( ROVs ; typically underwater). Unmanned aerial vehicles tend

  2. Low speed phaselock speed control system. [for brushless dc motor

    Science.gov (United States)

    Fulcher, R. W.; Sudey, J. (Inventor)

    1975-01-01

    A motor speed control system for an electronically commutated brushless dc motor is provided which includes a phaselock loop with bidirectional torque control for locking the frequency output of a high density encoder, responsive to actual speed conditions, to a reference frequency signal, corresponding to the desired speed. The system includes a phase comparator, which produces an output in accordance with the difference in phase between the reference and encoder frequency signals, and an integrator-digital-to-analog converter unit, which converts the comparator output into an analog error signal voltage. Compensation circuitry, including a biasing means, is provided to convert the analog error signal voltage to a bidirectional error signal voltage which is utilized by an absolute value amplifier, rotational decoder, power amplifier-commutators, and an arrangement of commutation circuitry.

  3. Comparison of computational modelling and field testing of a small wind turbine operating in unsteady flows

    Science.gov (United States)

    Bradney, D. R.; Evans, S. P.; Salles Pereira Da Costa, M.; Clausen, P. D.

    2016-09-01

    Small horizontal-axis wind turbines are likely to operate in a broad range of operating flow conditions, often in highly turbulent flow, due, in part, to their varied site placements. This paper compares the computational simulations of the performance of a 5 kW horizontal-axis wind turbine to detailed field measurements, with a particular focus on the impact of unsteady operating conditions on the drivetrain performance and generator output. Results indicate that the current Blade Element Momentum Theory based aerodynamic models under-predict the effect of high turbine yaw on the rotor torque, leading to a difference between predicted and measured shaft speed and power production. Furthermore, the results show discrepancies between the predicted instantaneous turbine yaw performance and measurements.

  4. Experimental study of controlled tip disturbance effect on flow asymmetry

    Science.gov (United States)

    Degani, David; Tobak, Murray

    1992-01-01

    The effect on the asymmetric mean flow observed on pointed bodies of revolution at incidence of changing the size and location of a controlled disturbance as well as changes in angle of attack and flow conditions are evaluated experimentally. Flow visualization and side-force measurements are carried out for a generic ogive-cylinder body inclined at high angle of attack in a low-speed wind tunnel. For all angles of attack tested (30-60 deg), minute changes in the size or location of the controlled disturbance result in finite changes in the asymmetric flow field, even to the extent of reversing the sign of the side force or becoming almost symmetric. The process is reversible; returning the wire to an original position likewise restores the corresponding flow field and mean side force. The variation of side force with continuous variation of a perturbation's size or location remains continuous and single valued, even in the incidence range of 50 to 60 deg, where 'bistable' behavior of the asymmetric flow field is observed.

  5. Receptivity of plane Poiseuille flow to local micro-vibration disturbance on wall

    Directory of Open Access Journals (Sweden)

    Wei-dong CAO

    2015-04-01

    Full Text Available The receptivity of plane Poiseuille flow to local single-period micro-vibration disturbances with different phases at the top and bottom walls was investigated through direct numerical simulation of three-dimensional incompressible Navier-Stokes equations. Results show that the disturbance presents a symmetrical distribution in the spanwise direction when the micro-vibration on the wall ends, and the initial disturbance velocities and spatial distribution of the disturbance structure are different at the top and bottom walls. The disturbance’s velocity, amplitude, and high- and low-speed streaks increase with time, and the amplitude of streamwise disturbance velocity is larger than those of spanwise and vertical disturbance velocities. However, no significant Tollmien-Schlichting wave was found in the flow field. The number of disturbance vortex cores gradually increases with the disturbance area. High-speed disturbance fluid concentrates near the wall and its normal velocity largely points to the wall, while low-speed disturbance fluid largely deviates from the wall. Furthermore, the streamwise velocity profiles near the top and bottom walls both become plump because of the existence of the disturbances, and the streamwise velocity profiles show a trend of evolving into turbulent velocity profiles. The shear stress near the wall increases significantly. The local micro-vibration disturbance on the wall in plane Poiseuille flow can induce the development of a structure similar to turbulent spots.

  6. Building a vehicle low-speed crash evaluation system suiting the road and trafifc conditions and the market demands of China%建立适合中国道路交通和市场需求的汽车低速碰撞评价体系

    Institute of Scientific and Technical Information of China (English)

    李兴虎; 李臣; 周炜; 王晋

    2013-01-01

    The world-wide implementation of vehicle low-speed crash test system reduces trafifc accidents, and plays an important role in automotive marketing and auto insurance. This paper analyzes the current situation of the vehicle low-speed crash test regulations of the Research Council for Automobile Repairs (the RCAR) and the American Insurance Institute for Highway Safety (the IIHS), of China, and of the other countries. Since there are no sufifcient accident records of the trafifc conditions, vehicle models and brands etc. in China, it is necessary to establish a vehicle low-speed crash test evaluation system suiting China’s situation according to the regulations of other advanced countries. Some measures can be that:1) recording vehicle makes and models, crash types, road conditions, and trafifc conditions during accident compensation;2) based on the records, determining key test parameters such as the crash speed, the overlap degree in a corner test, and the barrier height;3) developing hardware and software facilities for the evaluation system.%国际汽车低速碰撞试验评价体系的实施,在一定程度上减少了交通事故,对汽车营销、汽车保险也有重要作用。该文分析了中国以及国际组织RCAR(汽车维修研究委员会)和美国的IIHS (道路安全保险研究所,一般称美国公路安全协会)有关汽车低速碰撞试验规范。结果表明:中国在制定低速碰撞试验规范时,缺少汽车交通事故发生时的道路交通情况、车型和品牌的记录等。因此有必要参照国际相关规定,建立适合中国情况的汽车低速碰撞评价体系。主要措施有:1)碰撞事故理赔时,要记录车型、品牌、碰撞形式、道路交通情况;2)依据这些记录,确定碰撞车速、角碰撞的重叠度和壁障高度等参数;3)开发该评价体系所需的软硬件设施。

  7. Conical quarl swirl stabilized non-premixed flames: flame and flow field interaction

    KAUST Repository

    Elbaz, Ayman M.

    2017-09-19

    The flame-flow field interaction is studied in non-premixed methane swirl flames stabilized in quartz quarl via simultaneous measurements of the flow field using a stereo PIV and OH-PLIF at 5 KHz repetition rate. Under the same swirl intensity, two flames with different fuel jet velocity were investigated. The time-averaged flow field shows a unique flow pattern at the quarl exit, where two recirculation vortices are formed; a strong recirculation zone formed far from the quarl exit and a larger recirculation zone extending inside the quarl. However, the instantaneous images show that, the flow pattern near the quarl exit plays a vital role in the spatial location and structure of the reaction zone. In the low fuel jet velocity flame, a pair of vortical structures, located precisely at the corners of the quarl exit, cause the flame to roll up into the central region of low speed flow, where the flame sheet then tracks the axial velocity fluctuations. The vorticity field reveals a vortical structure surrounding the reaction zones, which reside on a layer of low compressive strain adjacent to that vortical structure. In the high fuel jet velocity flame, initially a laminar flame sheet resides at the inner shear layer of the main jet, along the interface between incoming fresh gas and high temperature recirculating gas. Further downstream, vortex breakdown alters the flame sheet path toward the central flame region. The lower reaction zones show good correlation to the regions of maximum vorticity and track the regions of low compressive strain associated with the inner shear layer of the jet flow. In both flames the reactions zones conform the passage of the large structure while remaining inside the low speed regions or at the inner shear layer.

  8. TURBULENCE TRANSPORT OF SURFACTANT SOLUTION FLOW DURING DRAG REDUCTION DEGENERATION

    Institute of Scientific and Technical Information of China (English)

    GU Wei-guo; WANG De-zhong

    2012-01-01

    Turbulence transport of surfactant solution flow during drag reduction degeneration is investigated experimentally in a two-dimensional channel.Particle Image Velocimetry (P1V) system is used to take two-dimensional velocity frames in the streamwise and wall-normal plane.The additive of surfactant is cetyltrimethyl ammonium chloride (CTAC) with the mass concentration of 25 ppm.Drag reduction degeneration happens in the CTAC solution flow,exhibiting the maximal drag reduction at Re =25000and losing drag reduction completely at Re =40 000.The velocity frames are statistically analyzed in four quadrants which are divided by the u -axis and v-axis.It is found that the phenomenon of“Zero Reynolds shear stress” is caused by the decrease of wallnormal fluctuations and its symmetrical distribution in quadrants.The increase of Reynolds number leads to the enhancement of turbulence burst phenomenon.During thc drag reduction degeneration,the CTAC solution flow contains both high turbulence intensity and drag reduction states.

  9. 空气湿度对矿用低速风洞的风速表检定结果影响%Analysis of air temperature and humidity on the impact of mining anemometer with a low-speed wind tunnel verification results

    Institute of Scientific and Technical Information of China (English)

    陈权; 张于; 卢从俊

    2013-01-01

      分析矿用低速风洞的工作原理,研究目前所使用的检定规程JJG(煤炭)01—96《矿用风速表》,发现湿度的变化影响空气密度的变化,而空气密度的改变直接影响风速表的检定结果。忽略了湿度对空气密度的影响,会影响风速表检定结果的准确性。%  This paper first introduces the current China's mining anemometer verification the basic situation, detailed analysis of the working principle of the mine low-speed wind tunnel. Based on the principle of this kind of work, we ware carefully studied mining anemometer VRof, The currently used VRof is JJG (coal) 01-96《mining anemometer》VRof, this statute ignored the impact of humidity on the verification results. In this paper, the effects of humidity study. The analysis found that changes in humidity will affect the changes in air density, and the air density changes directly affect the verification results of the anemometer. Ignoring the influence of the humidity of the air density will affect the accuracy of the anemometer verification results.

  10. 数控基准转换模式在大功率船用低速柴油机零件机架加工中的应用%Application of NC Benchmark Transformation in the Process of Frame of High-power and Low-speed Marine Diesel Engine Part Machining

    Institute of Scientific and Technical Information of China (English)

    陈涛

    2014-01-01

    Through the process analysis of frame of high power and low speed marine diesel engine’s part,and com-bined with large CNC gantry milling machine processing characteristics of cavity parts,cutting tools,fixture and CNC pro-gramming application of many fields,a set of frame's processing scheme of numerical control benchmark transformation model was formed,it can effectively avoid the risk for heavy machine tool operators work in height,made unified benchmark of parts machining,machining interference easy to see and control the man-machine interaction.%通过对大功率船用低速柴油机零件机架的工艺分析,结合大型数控龙门铣床对腔体类零件的加工特点,融合刀具、工装及数控编程等多领域技术,形成了一套数控基准转换模式的机架加工方案,其有效规避了大型机床操作工的登高作业风险,使零件加工基准统一,机床加工干涉透明,人机互动简单易控。

  11. A Dual-Plane PIV Study of Turbulent Heat Transfer Flows

    Science.gov (United States)

    Wernet, Mark P.; Wroblewski, Adam C.; Locke, Randy J.

    2016-01-01

    Thin film cooling is a widely used technique in turbomachinery and rocket propulsion applications, where cool injection air protects a surface from hot combustion gases. The injected air typically has a different velocity and temperature from the free stream combustion flow, yielding a flow field with high turbulence and large temperature differences. These thin film cooling flows provide a good test case for evaluating computational model prediction capabilities. The goal of this work is to provide a database of flow field measurements for validating computational flow prediction models applied to turbulent heat transfer flows. In this work we describe the application of a Dual-Plane Particle Image Velocimetry (PIV) technique in a thin film cooling wind tunnel facility where the injection air stream velocity and temperatures are varied in order to provide benchmark turbulent heat transfer flow field measurements. The Dual-Plane PIV data collected include all three components of velocity and all three components of vorticity, spanning the width of the tunnel at multiple axial measurement planes.

  12. Statistical analysis of turbulent super-streamwise vortices based on observations of streaky structures near the free surface in the smooth open channel flow

    Science.gov (United States)

    Zhong, Qiang; Chen, Qigang; Wang, Hao; Li, Danxun; Wang, Xingkui

    2016-05-01

    Long streamwise-elongated high- and low-speed streaks are repeatedly observed near the free surface in open channel flows in natural rivers and lab experiments. Super-streamwise vortex model has been proposed to explain this widespread phenomenon for quite some time. However, statistical evidence of the existence of the super-streamwise vortices as one type of coherent structures is still insufficient. Correlation and proper orthogonal decomposition (POD) analysis based on PIV experimental data in the streamwise-spanwise plane near the free surface in a smooth open channel flow are employed to investigate this topic. Correlation analysis revealed that the streaky structures appear frequently near the free surface and their occurrence probability at any spanwise position is equal. The spanwise velocity fluctuation usually flows from low-speed streaks toward high-speed streaks. The average spanwise width and spacing between neighboring low (or high) speed streaks are approximately h and 2h respectively. POD analysis reveals that there are streaks with different spanwise width in the instantaneous flow fields. Typical streamwise rotational movement can be sketched out directly based on the results from statistical analyses. Point-by-point analysis indicates that this pattern is consistent everywhere in the measurement window and is without any inhomogeneity in the spanwise direction, which reveals the essential difference between coherent structures and secondary flow cells. The pattern found by statistical analysis is consistent with the notion that the super-streamwise vortices exist universally as one type of coherent structure in open channel flows.

  13. Time-derivative preconditioning method for multicomponent flow

    Science.gov (United States)

    Housman, Jeffrey Allen

    A time-derivative preconditioned system of equations suitable for the numerical simulation of single component and multicomponent inviscid flows at all speeds is formulated. The system is shown to be hyperbolic in time and remain well-posed at low Mach numbers, allowing an efficient time marching solution strategy to be utilized from transonic to incompressible flow speeds. For multicomponent flow at low speed, a preconditioned nonconservative discretization scheme is described which preserves pressure and velocity equilibrium across fluid interfaces, handles sharp liquid/gas interfaces with large density ratios, while remaining well-conditioned for time marching methods. The method is then extended to transonic and supersonic flows using a hybrid conservative/nonconservative formulation which retains the pressure/velocity equilibrium property and converges to the correct weak solution when shocks are present. In order to apply the proposed model to complex flow applications, the overset grid methodology is used where the equations are transformed to a nonorthogonal curvilinear coordinate system and discretized on structured body-fitted curvilinear grids. The multicomponent model and its extension to homogeneous multiphase mixtures is discussed and the hyperbolicity of the governing equations is demonstrated. Low Mach number perturbation analysis is then performed on the system of equations and a local time-derivative preconditioning matrix is derived allowing time marching numerical methods to remain efficient at low speeds. Next, a particular time marching numerical method is presented along with three discretization schemes for the convective terms. These include a conservative preconditioned Roe type method, a nonconservative preconditioned Split Coefficient Matrix (SCM) method, and hybrid formulation which combines the conservative and nonconservative schemes using a simple switching function. A characteristic boundary treatment which includes time

  14. Inflectional instabilities in the wall region of bounded turbulent shear flows

    Science.gov (United States)

    Swearingen, Jerry D.; Blackwelder, Ron F.; Spalart, Philippe R.

    1987-01-01

    The primary thrust of this research was to identify one or more mechanisms responsible for strong turbulence production events in the wall region of bounded turbulent shear flows. Based upon previous work in a transitional boundary layer, it seemed highly probable that the production events were preceded by an inflectional velocity profile which formed on the interface between the low-speed streak and the surrounding fluid. In bounded transitional flows, this unstable profile developed velocity fluctuations in the streamwise direction and in the direction perpendicular to the sheared surface. The rapid growth of these instabilities leads to a breakdown and production of turbulence. Since bounded turbulent flows have many of the same characteristics, they may also experience a similar type of breakdown and turbulence production mechanism.

  15. Flow Control

    Science.gov (United States)

    2013-04-08

    an aerodynamic design. A few examples of this type of flow control are winglets , fins, or dimples on a golf ball. The other type of flow control is...represented the density states of the flow field. The first parameter was the composition of the regression vector, Θ j. This regression vector was...Development Using Proper Orthogonal De- composition and Volterra Theory. In AIAA 2003-1922, 2003. A. Mani, M. Wang, and P. Moin. Resolution requirements

  16. Rotating flow

    CERN Document Server

    Childs, Peter R N

    2010-01-01

    Rotating flow is critically important across a wide range of scientific, engineering and product applications, providing design and modeling capability for diverse products such as jet engines, pumps and vacuum cleaners, as well as geophysical flows. Developed over the course of 20 years' research into rotating fluids and associated heat transfer at the University of Sussex Thermo-Fluid Mechanics Research Centre (TFMRC), Rotating Flow is an indispensable reference and resource for all those working within the gas turbine and rotating machinery industries. Traditional fluid and flow dynamics

  17. 基于预处理HLLEW格式的全速域数值算法%Preconditioning HLLEW Scheme for Flows at All Mach Numbers

    Institute of Scientific and Technical Information of China (English)

    刘中玉; 张明锋; 郑冠男; 杨国伟

    2016-01-01

    Based on HLLEW ( Harten⁃Lax⁃Van Leer⁃Einfeldt⁃Wada) scheme, low speed preconditioning technology is introduced to develop a three⁃dimensional Navier⁃Stokes solver for flows at all Mach numbers. Low speed preconditioning techniques is introduced to reconstruct dissipative term in HLLEW scheme and preconditioning HLLEW scheme is proposed. Implicit time⁃marching method is constructed based on preconditioning Jacobian Matrix. Results of NACA 4412 incompressible flow and RAE 2822 transonic flow with preconditioning HLLEW scheme are compared with results by original method and experimental data. It shows that preconditioning HLLEW method improves accuracy and convergence rate for low speed flow. It can be applied for flows at all Mach numbers.%基于HLLEW( Harten⁃Lax⁃Van Leer⁃Einfeldt⁃Wada)格式引入预处理技术发展适合求解全速域流场的三维Navier⁃Stokes求解器。引入低速预处理技术,重新构造HLLEW格式的耗散项,给出预处理后的HLLEW格式,并根据预处理后的雅克比矩阵构造相应的隐式时间推进方程。利用预处理方法求解 NACA 4412低速不可压流动与RAE 2822跨声速可压缩流动,并与实验结果及原有方法的计算结果对比。结果表明:预处理HLLEW格式不仅提高低速不可压缩流动的计算效率和精度,也保持了对可压缩流动的处理能力,是一种适用于全速域流场数值模拟的有效方法。

  18. Network Flows

    Science.gov (United States)

    1988-12-01

    Researchers have suggested other solution strategies, using ideas from nonlinear progamming for solving this general separable convex cost flow problems. Some...plane methods and branch and bound procedures of integer programming, primal-dual methods of linear and nonlinear programming, and polyhedral methods...Combinatorial Optimization: Networks and Matroids), Bazaraa and Jarvis [1978] (Linear Programming and Network Flows), Minieka [1978] (Optimization Algorithms for

  19. Vortical flows

    CERN Document Server

    Wu, Jie-Zhi; Zhou, Ming-De

    2015-01-01

    This book is a comprehensive and intensive book for graduate students in fluid dynamics as well as scientists, engineers and applied mathematicians. Offering a systematic introduction to the physical theory of vortical flows at graduate level, it considers the theory of vortical flows as a branch of fluid dynamics focusing on shearing process in fluid motion, measured by vorticity. It studies vortical flows according to their natural evolution stages,from being generated to dissipated. As preparation, the first three chapters of the book provide background knowledge for entering vortical flows. The rest of the book deals with vortices and vortical flows, following their natural evolution stages. Of various vortices the primary form is layer-like vortices or shear layers, and secondary but stronger form is axial vortices mainly formed by the rolling up of shear layers.  Problems are given at the end of each chapter and Appendix, some for helping understanding the basic theories, and some involving specific ap...

  20. Study of the Standard k-ɛ Model for Tip Leakage Flow in an Axial Compressor Rotor

    Science.gov (United States)

    Gao, Yanfei; Liu, Yangwei; Zhong, Luyang; Hou, Jiexuan; Lu, Lipeng

    2016-12-01

    The standard k-ɛ model (SKE) and the Reynolds stress model (RSM) are employed to predict the tip leakage flow (TLF) in a low-speed large-scale axial compressor rotor. Then, a new research method is adopted to "freeze" the turbulent kinetic energy and dissipation rate of the flow field derived from the RSM, and obtain the turbulent viscosity using the Boussinesq hypothesis. The Reynolds stresses and mean flow field computed on the basis of the frozen viscosity are compared with the results of the SKE and the RSM. The flow field in the tip region based on the frozen viscosity is more similar to the results of the RSM than those of the SKE, although certain differences can be observed. This finding indicates that the non-equilibrium turbulence transport nature plays an important role in predicting the TLF, as well as the turbulence anisotropy.

  1. A new de-noising method for acoustic emission signal of rolling bearings with low speed based on morphological filtering in frequency domain%基于频域形态滤波的低速滚动轴承声发射信号降噪新方法

    Institute of Scientific and Technical Information of China (English)

    李修文; 阳建宏; 黎敏; 徐金梧

    2013-01-01

    声发射检测技术以其灵敏度高、频响范围宽、信息量大等优点,为机械故障诊断提供了一条新的检测途径,但应用于旋转机械设备时,容易混入各种有色噪声.当噪声频率与声发射信号重叠时,传统的降噪方法难以满足要求.将形态滤波应用到信号频域,可以有效消除有色噪声的干扰.根据声发射频响特性,对频谱进行拟合平滑高斯白噪声的影响,最后重构到时域.仿真和实际低速轴承信号表明此方法具有较好的降噪效果,有利于信号后续的处理和分析.%Acoustic emission technique provides a new measuring approach for machinery fault diagnosis because of its characteristics of high sensitivity, wide frequency response range and containing much information. An acoustic emission signal often is mixed with a variety of color noise when applied to a rotating machinery. Traditional noise reduction methods can not meet the measuring requirements when the frequencies of noise and those of acoustic emission signals overlap. Here, morphological filtering was applied to eliminate color noise in frequency domain. According to the acoustic emission frequency response characteristic, a spectrum was fitted in order to smooth white Gaussian noise. Finally, a time domain waveform was reconstructed. The simulation results and the real signals of rolling bearings with low speed showed that the proposed methodology can achieve good effect of noise reduction, and is beneficial to the subsequent processing and analysis of signals.

  2. Flow characteristics over NACA4412 airfoil at low Reynolds number

    Directory of Open Access Journals (Sweden)

    Genç Mustafa Serdar

    2016-01-01

    Full Text Available In this study, the flow phenomena over NACA4412 were experimentally observed at various angle of attack and Reynolds number of 25000, 50000 and 75000, respectively. NACA4412 airfoil was manufactured at 3D printer and each tips of the wing were closed by using plexiglas to obtain two-dimensional airfoil. The experiments were conducted at low speed wind tunnel. The force measurement and hot-wire experiments were conducted to obtain data so that the flow phenomenon at the both top and bottom of the airfoil such as the flow separation and vortex shedding were observed. Also, smoke-wire experiment was carried out to visualize the surface flow pattern. After obtaining graphics from both force measurement experiment and hot-wire experiment compared with smoke wire experiment, it was noticed that there is a good coherence among the experiments. It was concluded that as Re number increased, the stall angle increased. And the separation bubble moved towards leading edge over the airfoil as the angle of attack increased.

  3. Fluidic actuators for active flow control on airframe

    Science.gov (United States)

    Schueller, M.; Weigel, P.; Lipowski, M.; Meyer, M.; Schlösser, P.; Bauer, M.

    2016-04-01

    One objective of the European Projects AFLoNext and Clean Sky 2 is to apply Active Flow Control (AFC) on the airframe in critical aerodynamic areas such as the engine/wing junction or the outer wing region for being able to locally improve the aerodynamics in certain flight conditions. At the engine/wing junction, AFC is applied to alleviate or even eliminate flow separation at low speeds and high angle of attacks likely to be associated with the integration of underwing- mounted Ultra High Bypass Ratio (UHBR) engines and the necessary slat-cut-outs. At the outer wing region, AFC can be used to allow more aggressive future wing designs with improved performance. A relevant part of the work on AFC concepts for airframe application is the development of suitable actuators. Fluidic Actuated Flow Control (FAFC) has been introduced as a Flow Control Technology that influences the boundary layer by actively blowing air through slots or holes out of the aircraft skin. FAFC actuators can be classified by their Net Mass Flux and accordingly divided into ZNMF (Zero Net Mass Flux) and NZNMF (Non Zero Net-Mass-Flux) actuators. In the frame of both projects, both types of the FAFC actuator concepts are addressed. In this paper, the objectives of AFC on the airframe is presented and the actuators that are used within the project are discussed.

  4. Water-in-Water Droplets by Passive Microfluidic Flow Focusing.

    Science.gov (United States)

    Moon, Byeong-Ui; Abbasi, Niki; Jones, Steven G; Hwang, Dae Kun; Tsai, Scott S H

    2016-04-05

    We present a simple microfluidic system that generates water-in-water, aqueous two phase system (ATPS) droplets, by passive flow focusing. ATPS droplet formation is achieved by applying weak hydrostatic pressures, with liquid-filled pipette tips as fluid columns at the inlets, to introduce low speed flows to the flow focusing junction. To control the size of the droplets, we systematically vary the interfacial tension and viscosity of the ATPS fluids and adjust the fluid column height at the fluid inlets. The size of the droplets scales with a power law of the ratio of viscous stresses in the two ATPS phases. Overall, we find a drop size coefficient of variation (CV; i.e., polydispersity) of about 10%. We also find that when drops form very close to the flow focusing junction, the drops have a CV of less than 1%. Our droplet generation method is easily scalable: we demonstrate a parallel system that generates droplets simultaneously and improves the droplet production rate by up to one order of magnitude. Finally, we show the potential application of our system for encapsulating cells in water-in-water emulsions by encapsulating microparticles and cells. To the best of our knowledge, our microfluidic technique is the first that forms low interfacial tension ATPS droplets without applying external perturbations. We anticipate that this simple approach will find utility in drug and cell delivery applications because of the all-biocompatible nature of the water-in-water ATPS environment.

  5. Fluid flow dynamics in MAS systems.

    Science.gov (United States)

    Wilhelm, Dirk; Purea, Armin; Engelke, Frank

    2015-08-01

    The turbine system and the radial bearing of a high performance magic angle spinning (MAS) probe with 1.3mm-rotor diameter has been analyzed for spinning rates up to 67kHz. We focused mainly on the fluid flow properties of the MAS system. Therefore, computational fluid dynamics (CFD) simulations and fluid measurements of the turbine and the radial bearings have been performed. CFD simulation and measurement results of the 1.3mm-MAS rotor system show relatively low efficiency (about 25%) compared to standard turbo machines outside the realm of MAS. However, in particular, MAS turbines are mainly optimized for speed and stability instead of efficiency. We have compared MAS systems for rotor diameter of 1.3-7mm converted to dimensionless values with classical turbomachinery systems showing that the operation parameters (rotor diameter, inlet mass flow, spinning rate) are in the favorable range. This dimensionless analysis also supports radial turbines for low speed MAS probes and diagonal turbines for high speed MAS probes. Consequently, a change from Pelton type MAS turbines to diagonal turbines might be worth considering for high speed applications. CFD simulations of the radial bearings have been compared with basic theoretical values proposing considerably smaller frictional loss values. The discrepancies might be due to the simple linear flow profile employed for the theoretical model. Frictional losses generated inside the radial bearings result in undesired heat-up of the rotor. The rotor surface temperature distribution computed by CFD simulations show a large temperature gradient over the rotor.

  6. Three dimensional simulation of compressible and incompressible flows through the finite element method; Simulacao tridimensional de escoamentos compressiveis e incompressiveis atraves do metodo dos elementos finitos

    Energy Technology Data Exchange (ETDEWEB)

    Costa, Gustavo Koury

    2004-11-15

    Although incompressible fluid flows can be regarded as a particular case of a general problem, numerical methods and the mathematical formulation aimed to solve compressible and incompressible flows have their own peculiarities, in such a way, that it is generally not possible to attain both regimes with a single approach. In this work, we start from a typically compressible formulation, slightly modified to make use of pressure variables and, through augmenting the stabilising parameters, we end up with a simplified model which is able to deal with a wide range of flow regimes, from supersonic to low speed gas flows. The resulting methodology is flexible enough to allow for the simulation of liquid flows as well. Examples using conservative and pressure variables are shown and the results are compared to those published in the literature, in order to validate the method. (author)

  7. Effects of Low Reynolds Number on Wake-Generated Unsteady Flow of an Axial-Flow Turbine Rotor

    Directory of Open Access Journals (Sweden)

    Matsunuma Takayuki

    2005-01-01

    Full Text Available The unsteady flow field downstream of axial-flow turbine rotors at low Reynolds numbers was investigated experimentally using hot-wire probes. Reynolds number, based on rotor exit velocity and rotor chord length Re out,RT , was varied from 3.2× 10 4 to 12.8× 10 4 at intervals of 1.0× 10 4 by changing the flow velocity of the wind tunnel. The time-averaged and time-dependent distributions of velocity and turbulence intensity were analyzed to determine the effect of Reynolds number. The reduction of Reynolds number had a marked influence on the turbine flow field. The regions of high turbulence intensity due to the wake and the secondary vortices were increased dramatically with the decreasing Reynolds number. The periodic fluctuation of the flow due to rotor-stator interaction also increased with the decreasing Reynolds number. The energy-dissipation thickness of the rotor midspan wake at the low Reynolds number Re out,RT =3.2× 10 4 was 1.5 times larger than that at the high Reynolds number Re out,RT =12.8× 10 4 . The curve of the −0.2 power of the Reynolds number agreed with the measured energy-dissipation thickness at higher Reynolds numbers. However, the curve of the −0.4 power law fitted more closely than the curve of the −0.2 power law at lower Reynolds numbers below 6.4× 10 4 .

  8. Collision partner selection schemes in DSMC: From micro/nano flows to hypersonic flows

    Science.gov (United States)

    Roohi, Ehsan; Stefanov, Stefan

    2016-10-01

    The motivation of this review paper is to present a detailed summary of different collision models developed in the framework of the direct simulation Monte Carlo (DSMC) method. The emphasis is put on a newly developed collision model, i.e., the Simplified Bernoulli trial (SBT), which permits efficient low-memory simulation of rarefied gas flows. The paper starts with a brief review of the governing equations of the rarefied gas dynamics including Boltzmann and Kac master equations and reiterates that the linear Kac equation reduces to a non-linear Boltzmann equation under the assumption of molecular chaos. An introduction to the DSMC method is provided, and principles of collision algorithms in the DSMC are discussed. A distinction is made between those collision models that are based on classical kinetic theory (time counter, no time counter (NTC), and nearest neighbor (NN)) and the other class that could be derived mathematically from the Kac master equation (pseudo-Poisson process, ballot box, majorant frequency, null collision, Bernoulli trials scheme and its variants). To provide a deeper insight, the derivation of both collision models, either from the principles of the kinetic theory or the Kac master equation, is provided with sufficient details. Some discussions on the importance of subcells in the DSMC collision procedure are also provided and different types of subcells are presented. The paper then focuses on the simplified version of the Bernoulli trials algorithm (SBT) and presents a detailed summary of validation of the SBT family collision schemes (SBT on transient adaptive subcells: SBT-TAS, and intelligent SBT: ISBT) in a broad spectrum of rarefied gas-flow test cases, ranging from low speed, internal micro and nano flows to external hypersonic flow, emphasizing first the accuracy of these new collision models and second, demonstrating that the SBT family scheme, if compared to other conventional and recent collision models, requires smaller

  9. Massive separation of turbulent Couette flow in a one-sided expansion channel

    Energy Technology Data Exchange (ETDEWEB)

    El Khoury, George K. [Department of Marine Technology, Norwegian University of Science and Technology, Trondheim NO-7491 (Norway); Andersson, Helge I.; Barri, Mustafa [Department of Energy and Process Engineering, Norwegian University of Science and Technology, Trondheim NO-7491 (Norway); Pettersen, Bjornar, E-mail: bjornar.pettersen@ntnu.n [Department of Marine Technology, Norwegian University of Science and Technology, Trondheim NO-7491 (Norway)

    2010-06-15

    Direct numerical simulation has been performed to study wall-driven flow over a backward-facing step at Reynolds number Re=5200 based on the step height h and the upper-wall velocity U{sub w}. The flow configuration consisted of a step with height equal to that of the upstream channel yielding an expansion ratio 2:1. Instantaneous enstrophy contours revealed the formation of Kelvin-Helmholtz instabilities downstream of the step. Intense velocity and vorticity fluctuations were generated in the shear-layer formed between the bulk flow and the massive recirculation zone in the lee of the step. Extraordinarily high turbulence levels persisted in the center region even 7.5h downstream of the step, i.e. where the separated shear-layer reattached to the wall. A fully redeveloped Couette flow cannot be reached in the downstream part of the channel due to the principle of mass conservation. The local wall pressure coefficient gave evidence of an adverse pressure gradient in the recovery region, where a Couette-Poiseuille flow type prevailed.

  10. Numerical study of cross flow fan performance in an indoor air conditioning unit

    Science.gov (United States)

    Yet, New Mei; Raghavan, Vijay R.; Chinc, W. M.

    2012-06-01

    The cross flow fan is a unique type of turbo machinery where the air stream flows transversely across the impeller, passing the blades twice. Due to its complex geometry, and highly turbulent and unsteady air-flow, a numerical method is used in this work to conduct the characterization study on the performance of a cross flow fan. A 2D cross-sectional model of a typical indoor air conditioning unit has been chosen for the simulation instead of a three dimensional 3D model due to the highly complex geometry of the fan. The simplified 2D model has been validated with experiments where it is found that the RMS error between the simulation and experimental results is less than 7%. The important parameters that affect the cross flow fan performance, i.e. the internal and external blade angles, the blade thickness, and the casing design, are analyzed in this study. The formation of an eccentric vortex is observed within the impeller.

  11. Liquid Steel at Low Pressure: Experimental Investigation of a Downward Water Air Flow

    Science.gov (United States)

    Thumfart, Maria

    2016-07-01

    In the continuous casting of steel controlling the steel flow rate to the mould is critical because a well-defined flow field at the mould level is essential for a good quality of the cast product. The stopper rod is a commonly used device to control this flow rate. Agglomeration of solid material near the stopper rod can lead to a reduced cross section and thus to a decreased casting speed or even total blockage (“clogging”). The mechanisms causing clogging are still not fully understood. Single phase considerations of the flow in the region of the stopper rod result in a low or even negative pressure at the smallest cross section. This can cause degassing of dissolved gases from the melt, evaporation of alloys and entrainment of air through the porous refractory material. It can be shown that the degassing process in liquid steel is taking place mainly at the stopper rod tip and its surrounding. The steel flow around the stopper rod tip is highly turbulent. In addition refractory material has a low wettability to liquid steel. So the first step to understand the flow situation and transport phenomena which occur near the stopper is to understand the behaviour of this two phase (steel, gas) flow. To simulate the flow situation near the stopper rod tip, water experiments are conducted using a convergent divergent nozzle with three different wall materials and three different contact angles respectively. These experiments show the high impact of the wettability of the wall material on the actual flow structure at a constant gas flow rate.

  12. Drag measurements on a laminar-flow body of revolution in the 13-inch magnetic suspension and balance system

    Science.gov (United States)

    Dress, David A.

    1989-01-01

    Low speed wind tunnel drag force measurements were taken on a laminar flow body of revolution free of support interference. This body was tested at zero incidence in the NASA Langley 13 in. Magnetic Suspension and Balance System (MSBS). The primary objective of these tests was to substantiate the drag force measuring capabilities of the 13 in. MSBS. The drag force calibrations and wind-on repeatability data provide a means of assessing these capabilities. Additional investigations include: (1) the effects of fixing transition; (2) the effects of fins installed in the tail; and (3) surface flow visualization using both liquid crystals and oil flow. Also two simple drag prediction codes were used to assess their usefulness in estimating overall body drag.

  13. Acceleration of inertial particles in wall bounded flows: DNS and LES with stochastic modelling of the subgrid acceleration

    Energy Technology Data Exchange (ETDEWEB)

    Zamansky, Remi; Vinkovic, Ivana; Gorokhovski, Mikhael, E-mail: ivana.vinkovic@univ-lyonl.fr [Laboratoire de Mecanique des Fluides et d' Acoustique CNRS UMR 5509 Ecole Centrale de Lyon, 36, av. Guy de Collongue, 69134 Ecully Cedex (France)

    2011-12-22

    Inertial particle acceleration statistics are analyzed using DNS for turbulent channel flow. Along with effects recognized in homogeneous isotropic turbulence, an additional effect is observed due to high and low speed vortical structures aligned with the channel wall. In response to those structures, particles with moderate inertia experience strong longitudinal acceleration variations. DNS is also used in order to assess LES-SSAM (Subgrid Stochastic Acceleration Model), in which an approximation to the instantaneous non-filtered velocity field is given by simulation of both, filtered and residual, accelerations. This approach allow to have access to the intermittency of the flow at subgrid scale. Advantages of LES-SSAM in predicting particle dynamics in the channel flow at a high Reynolds number are shown.

  14. Stereoscopic PIV measurements of the flow field in a turbine cascade

    Science.gov (United States)

    Tian, Yangtao; Ma, Hongwei; Ma, Rong

    2017-02-01

    This paper presents experimental measurements of the flow field in a Low-speed Turbine Cascade using a stereoscopic particle-image velocimetry (SPIV). During the measurements, a pair of frame-straddling-based CCD cameras were configured at different sides of the laser light sheet, and appropriate tracing particles (DEHS) were employed. The measurements were conducted at the incidence angle of 0 degree and exit Reynolds number of 1.7 × 105 with the tip clearance 1.18% of blade chord. The tip flow features, such as the evolution and breakdown of tip leakage vortex, the horseshoe vortex, turbulence characteristics of tip leakage flow, were studied for the flow field analysis. The results showed that the tip leakage flow/vortex mainly dominate flow fields in the tip region. The tip leakage vortex performs as a concentrated vortex before its breaking down and splitting into small vortices. The highest turbulence intensity mainly occurs in the tip region along with the trajectory of tip leakage vortex, and when the vortex breaks down, the turbulence intensity reduces rapidly. Additionally, the SPIV with this configuration also shows an advantage in investigating the flow structures and mechanism inside the turbine cascade.

  15. Lubrication Flows.

    Science.gov (United States)

    Papanastasiou, Tasos C.

    1989-01-01

    Discusses fluid mechanics for undergraduates including the differential Navier-Stokes equations, dimensional analysis and simplified dimensionless numbers, control volume principles, the Reynolds lubrication equation for confined and free surface flows, capillary pressure, and simplified perturbation techniques. Provides a vertical dip coating…

  16. Evolutions of hairpin vortexes over a superhydrophobic surface in turbulent boundary layer flow

    Science.gov (United States)

    Zhang, Jingxian; Tian, Haiping; Yao, Zhaohui; Hao, Pengfei; Jiang, Nan

    2016-09-01

    Turbulent flows over a superhydrophobic surface and a smooth surface have been measured and studied by particle image velocimetry technology at Reθ = 990. The Reynolds shear stress distributions over the two surfaces are significantly different. Specifically, for the superhydrophobic surface, the Reynolds shear stress is suppressed in the near-wall region (y/δ curve. Evolutions of hairpin vortexes are analyzed to interpret differences in the Reynolds shear stress, based on some comparisons in the low-speed streaks and Q2/Q4 (ejection/sweep) events. The results show that, in the near wall region, the turbulent coherent structures (low-speed streaks and hairpin vortex) over the superhydrophobic surface are more stable and flat, due to the suppression in the strength and the lifting effect of the hairpin vortex. In the outer region, the superhydrophobic surface lifts the hairpin vortex away from the wall with a value of 0.14δ in our experiment, which makes the Q4 events occur further from the wall and contribute less to skin friction.

  17. An experimental investigation of the generation and consequences of acoustic waves in an axial flow compressor Large axial spacings between blade rows

    Science.gov (United States)

    Parker, R.; Stoneman, S. A. T.

    1985-03-01

    The excitation of acoustic waves by vortex shedding from the inlet guide vanes in the annulus of a single-stage, low-speed axial-flow compressor test rig is investigated experimentally, in an effort to examine the assumptions made in the study of Parker (1984) and to provide data for mathematical models of these phenomena. The experimental setup and the transducers used to measure the operating and acoustic parameters are described in detail and illustrated with photographs and drawings, and the results are presented graphically. It is found that each mode excited can be associated with several excitation frequencies of the rotor blades, indicating forced blade vibration due to acoustic resonances.

  18. EXPERIMENTAL INVESTIGATION FOR THE EFFECT OF ROTATION ON THREE-DIMENSIONAL FLOW FIELD IN FILM-COOLED TURBINE

    Institute of Scientific and Technical Information of China (English)

    YUAN Feng; ZHU Xiaocheng; DU Zhaohui

    2007-01-01

    An experimental investigation of three-dimensional flow field in a film-cooled turbine model is carried out by using particle image velocimeter (PIV) in a low-speed wind tunnel. The effects of different blowing ratios (M=1.5, 2) on the flow field are studied. The experimental results reveal the classical phenomena of the formation of kidney vortex pair and secondary flow in wake region behind the jet hole. And the changes of the kidney vortex pair and the wake at different locations away from the hole on the suction and pressure sides are also studied. Compared with the flow field in stationary cascade, there are centrifugal force and Coriolis force existing in the flow field of rotating turbine, and these forces bring the radial velocity in the jet flow. The effect of rotation on the flow field of the pressure side is more distinct than that on the suction side from the measured flow fields in Y-Z plane and radial velocity contours. The increase of blowing ratio makes the kidney vortex pair and the secondary flow in the wake region stronger and makes the range of the wake region enlarged.

  19. PRELIMINARY DESIGN OF OSCILLATORY FLOW BIODIESEL REACTOR FOR CONTINUOUS BIODIESEL PRODUCTION FROM JATROPHA TRIGLYCERIDES

    Directory of Open Access Journals (Sweden)

    AZHARI T. I. MOHD. GHAZI

    2008-08-01

    Full Text Available The concept of a continuous process in producing biodiesel from jatropha oil by using an Oscillatory Flow Biodiesel Reactor (OFBR is discussed in this paper. It has been recognized that the batch stirred reactor is a primary mode used in the synthesis of biodiesel. However, pulsatile flow has been extensively researcehed and the fundamental principles have been successfully developed upon which its hydrodynamics are based. Oscillatory flow biodiesel reactor offers precise control of mixing by means of the baffle geometry and pulsation which facilitates to continuous operation, giving plug flow residence time distribution with high turbulence and enhanced mass and heat transfer. In conjunction with the concept of reactor design, parameters such as reactor dimensions, the hydrodynamic studies and physical properties of reactants must be considered prior to the design work initiated recently. The OFBR reactor design involves the use of simulation software, ASPEN PLUS and the reactor design fundamentals. Following this, the design parameters shall be applied in fabricating the OFBR for laboratory scale biodiesel production.

  20. Comparison of PDF and Moment Closure Methods in the Modeling of Turbulent Reacting Flows

    Science.gov (United States)

    Norris, Andrew T.; Hsu, Andrew T.

    1994-01-01

    In modeling turbulent reactive flows, Probability Density Function (PDF) methods have an advantage over the more traditional moment closure schemes in that the PDF formulation treats the chemical reaction source terms exactly, while moment closure methods are required to model the mean reaction rate. The common model used is the laminar chemistry approximation, where the effects of turbulence on the reaction are assumed negligible. For flows with low turbulence levels and fast chemistry, the difference between the two methods can be expected to be small. However for flows with finite rate chemistry and high turbulence levels, significant errors can be expected in the moment closure method. In this paper, the ability of the PDF method and the moment closure scheme to accurately model a turbulent reacting flow is tested. To accomplish this, both schemes were used to model a CO/H2/N2- air piloted diffusion flame near extinction. Identical thermochemistry, turbulence models, initial conditions and boundary conditions are employed to ensure a consistent comparison can be made. The results of the two methods are compared to experimental data as well as to each other. The comparison reveals that the PDF method provides good agreement with the experimental data, while the moment closure scheme incorrectly shows a broad, laminar-like flame structure.

  1. Analytical models for flow control in subsonic and supersonic diffusing flow paths using steady blowing and suction

    Science.gov (United States)

    Sarimurat, Mehmet Nasir

    Flow blowing/suction has multiple beneficial effects on the performance of axial flow compressors. In both low speed and high speed compressors a small amount of flow blowing and/or suction can be applied in the region of adverse pressure gradient to control the boundary layer separation and obtain high pressure ratio across the compressor. On the other hand in high speed compressors where a passage shock is present inside the passage, flow blowing/suction can also be used to manage the shock location inside the passage and increase the operating range of the compressor. In the first part of this study, an analytical model based on the integral method for boundary layer with flow blowing in incompressible flows is developed that shows the effect of mass, momentum, velocity magnitude and injection angle of the blowing flow on the behavior of the boundary layer. According to the model the change in the boundary layer momentum thickness across the blowing location is linear function of the momentum of the blowing flow and exponential function of the velocity of the blowing flow. Also if the size of the blowing slot and the velocity of the blown flow are kept constant, when the amount of the blown flow is increased by increasing the blowing angle, there is an "optimum" angle that maximizes the decrease in the momentum thickness across the blowing station. This angle is a function of the velocity ratio and it reaches an asymptotic value of around 40°. The model also shows that the change in the trailing-edge momentum thickness is an exponential function of the change in the momentum thickness across the blowing location. The developed modeled is confirmed for the NACA-65-410 low speed cascade using Computational Fluid Dynamics and a good agreement between the theory and CFD is obtained. In the second part of the thesis a quasi-1D inviscid and compressible flow theory in a converging/diverging flow passage is presented that can predict the amount of flow blowing or

  2. Flow Separation

    Science.gov (United States)

    1975-11-01

    Born, Constantin Caratheodory, Richard Couiant, Kurt Friedrichs, Werner Heisenberg, Gustav Herglotz, Erich von Hoist, Pascual Jordan, Walther Nernst...existence of these two flow regimes in boundary layers was discovered by PRANDTL when EIFFEL [8] published in 1912 his measurements on the drag of...simultaneously by G. EIFFEL in Paris and became so successful that other wind tunnels were modelled after it in many countries. Fig. 18 gives an impression of

  3. Media Flow

    DEFF Research Database (Denmark)

    Kabel, Lars

    2016-01-01

    News and other kinds of journalistic stories, 16-17 hours a day, all year round, on all platforms, also the moderated social media. The key research thesis behind this article is that the continuous and speedy stream of news stories and media content now is becoming the centre of the production...... processes and the value creation in converged multimedia newsrooms. The article identify new methods and discuss editorial challenges in handling media flow....

  4. Numerical calculation of turbomachinery cascade flows

    Science.gov (United States)

    Liu, Feng

    three-dimensional vortex transport within a cascade passage. &Numerical results of secondary flow developments agree qualitatively with experiment. The method for the Reynolds-averaged Navier-Stokes equations was tested for two-dimensional flows. Perfect agreement with the Blasius solution was obtained for low-speed laminar flow over a flat plate. *Results for a turbulent flow over a flat plate compare well with empirical correlations. -The method is used to calculate the flows at mid-span through the same low pressure turbine cascade for which the Euler method was tested. Calculated results compare well with experimental data not only at the design condition but also at off-design conditions. Skin friction plots show separation bubbles which agree with experiments.

  5. Analysis of Coupled Seals, Secondary and Powerstream Flow Fields in Aircraft and Aerospace Turbomachines

    Science.gov (United States)

    Athavale, M. M.; Ho, Y. H.; Prezekwas, A. J.

    2005-01-01

    Higher power, high efficiency gas turbine engines require optimization of the seals and secondary flow systems as well as their impact on the powerstream. This work focuses on two aspects: 1. To apply the present day CFD tools (SCISEAL) to different real-life secondary flow applications from different original equipment manufacturers (OEM s) to provide feedback data and 2. Develop a computational methodology for coupled time-accurate simulation of the powerstream and secondary flow with emphasis on the interaction between the disk-cavity and rim seals flows with the powerstream (SCISEAL-MS-TURBO). One OEM simulation was of the Allison Engine Company T-56 turbine drum cavities including conjugate heat transfer with good agreement with data and provided design feedback information. Another was the GE aspirating seal where the 3-D CFD simulations played a major role in analysis and modification of that seal configuration. The second major objective, development of a coupled flow simulation capability was achieved by using two codes MS-TURBO for the powerstream and SCISEAL for the secondary flows with an interface coupling algorithm. The coupled code was tested against data from three differed configurations: 1. bladeless-rotor-stator-cavity turbine test rig, 2. UTRC high pressure turbine test rig, and, 3. the NASA Low-Speed-Air Compressor rig (LSAC) with results and limitations discussed herein.

  6. On the properties and mechanisms of microjet arrays in crossflow for the control of flow separation

    Science.gov (United States)

    Fernandez, Erik J.

    By utilizing passive and active methods of flow control, the aerodynamic performance of external and internal components can be greatly improved. Recently however, the benefits of applying active flow control methods to turbomachinery components for improved fuel efficiency, reduced engine size, and greater operational envelope has sparked a renewed interest in some of these flow control techniques. The more attractive of these, is active control in the form of jets in cross flow. With their ability to be turned on and off, as well as their negligible effect on drag when not being actuated, they are well suited for applications such as compressor and turbine blades, engine inlet diffusers, internal engine passages, and general external aerodynamics. This study consists of two parts. The first is the application of active control on a low-pressure turbine (LPT) cascade to determine the effectiveness of microjet actuators on flow separation at relatively low speeds. The second study, motivated by the first, involves a parametric study on a more canonical model to examine the effects of various microjet parameters on the efficacy of separation control and to provide a better understanding of the relevant flow physics governing this control approach. With data obtained from velocity measurements across the wide parametric range, correlations for the growth of the counter-rotating vortex pairs generated by these actuators are deduced. From the information and models obtained throughout the study, basic suggestions for microjet actuator design are presented.

  7. Wavelet analysis of hemispheroid flow separation toward understanding human vocal fold pathologies

    Science.gov (United States)

    Plesniak, Daniel H.; Carr, Ian A.; Bulusu, Kartik V.; Plesniak, Michael W.

    2014-11-01

    Physiological flows observed in human vocal fold pathologies, such as polyps and nodules, can be modeled by flow over a wall-mounted protuberance. The experimental investigation of flow separation over a surface-mounted hemispheroid was performed using particle image velocimetry (PIV) and measurements of surface pressure in a low-speed wind tunnel. This study builds on the hypothesis that the signatures of vortical structures associated with flow separation are imprinted on the surface pressure distributions. Wavelet decomposition methods in one- and two-dimensions were utilized to elucidate the flow behavior. First, a complex Gaussian wavelet was used for the reconstruction of surface pressure time series from static pressure measurements acquired from ports upstream, downstream, and on the surface of the hemispheroid. This was followed by the application of a novel continuous wavelet transform algorithm (PIVlet 1.2) using a 2D-Ricker wavelet for coherent structure detection on instantaneous PIV-data. The goal of this study is to correlate phase shifts in surface pressure with Strouhal numbers associated with the vortex shedding. Ultimately, the wavelet-based analytical framework will be aimed at addressing pulsatile flows. This material is based in part upon work supported by the National Science Foundation under Grant Number CBET-1236351, and GW Center for Biomimetics and Bioinspired Engineering (COBRE).

  8. Experimental characterization of transitional unsteady flow inside graft-to-vein junction

    Science.gov (United States)

    Arslan, Nurullah

    1999-12-01

    Turbulent flow measurements were conducted inside an upscaled end-to-side model of a human arteriovenous graft using laser Doppler anemometry under steady and pulsatile flow conditions. This research is clinically relevant because turbulence and local fluid dynamic factors such as wall shear stress have been implicated as localization factors for intimal hyperplasia, the main cause of arteriovenous graft failure. This research is the first experimental study measuring the turbulence level and Reynolds stresses quantitatively inside an in vitro model representing an arteriovenous graft under pulsatile flow conditions. The turbulence intensity, Reynolds stresses, and mean velocities have been measured for steady and pulsatile flow. Reynolds numbers for steady flow were 1060, 1820, 2530 and 2720. The peak, mean and minimum Reynolds numbers were 2470, 1762 and 1198 for the pulsatile flow, respectively. The flow division was 90% entering from the graft inlet and 10% entering from the distal vein segment for steady flow measurements. It was 85% entering from the graft inlet and 15% entering from the distal vein segment for pulsatile flow measurements. Measurements were made thirteen axial locations in the plane of the bifurcation at the venous anastomosis. At high Reynolds numbers (>2000), the velocity profiles were blunt at the inlet of the arteriovenous graft. High turbulent fluctuations and Reynolds stresses were found in the proximal vein segment opposite to the vein side of the anastomosis for steady and pulsatile flows. Steady flow fluctuation values were 20-30% larger than pulsatile flow values for the same instantaneous Reynolds number. The highest value of the Reynolds stress was found to be 2080 and 1400 dynes/cm2 steady and pulsatile flow, respectively. A separation region was observed at the toe side of the arteriovenous graft. Strong secondary flows were found at the inlet to and inside the proximal vein segment under steady flow conditions. The results of

  9. Flow and Flow Decay of Refractory Castables

    Institute of Scientific and Technical Information of China (English)

    CHEN Zhiqiang; Bjom Myhre; Bjorn Sandberg

    2003-01-01

    Installation of refractoty castables depend not only on flow, but also on how soon the flow is lost because of setting. The loss of flow (flow decay) has always been one of the main problems of refractory castable manufacturers,a problem that has not been too well described in literature. The flow decay has been studied for a castable system based on alumina, pointing out some general trends. The flow decay was found very temperature sensitive, being strongly accelerated by termperature increases. To compensate for excessive flow loss, a retarder like citric acid may be used. Thus flow decay was measured as a function of citric acid (retarder) addition at 35 ℃ .

  10. A 2D Simulation of the Flow Separation Control over a NACA0015 Airfoil Using a Synthetic Jet Actuator

    Science.gov (United States)

    Boukenkoul, M. A.; Li, F. C.; Aounallah, M.

    2017-03-01

    The present study aims to investigate numerically the flow control possibility using a synthetic jet actuation over a bi-dimensional NACA0015 airfoil manoeuvring at a highly turbulent flow (8.9e105 Reynolds to chord number). The 2-D flow behaviour was computed using the ANSYS Fluent commercial code. The so-called Reynolds Averaged Navier-Stocks (RANS) approach has been tested for one (Spalat-Allmaras S-A) and two (K-ε) transport equations for the turbulence modelling. Both present a weakness to predict the stall angle effectively. The S-A lift coefficient slope seems to be the closest to the experimental data. The synthetic jet control exhibits an extraordinary lift coefficient enhancement at high Angles Of Attack (AOA) but seems to be less obvious at low AOA, where the flow is still attached. A synthetic jet of a Strouhal (St = 2) and momentum (Cμ of 0.56%), delays the stall onset from 15 to 19deg with enhancing the lift coefficient by 40%. The actual work has been enriched by studying the effect of the jet’s frequency and momentum on the lift temporal signal. Also, the interaction between the mean flow and the synthetic jet structures topology was undertaken.

  11. Development and numerical analysis of low specific speed mixed-flow pump

    Science.gov (United States)

    Li, H. F.; Huo, Y. W.; Pan, Z. B.; Zhou, W. C.; He, M. H.

    2012-11-01

    With the development of the city, the market of the mixed flow pump with large flux and high head is prospect. The KSB Shanghai Pump Co., LTD decided to develop low speed specific speed mixed flow pump to meet the market requirements. Based on the centrifugal pump and axial flow pump model, aiming at the characteristics of large flux and high head, a new type of guide vane mixed flow pump was designed. The computational fluid dynamics method was adopted to analyze the internal flow of the new type model and predict its performances. The time-averaged Navier-Stokes equations were closed by SST k-ω turbulent model to adapt internal flow of guide vane with larger curvatures. The multi-reference frame(MRF) method was used to deal with the coupling of rotating impeller and static guide vane, and the SIMPLEC method was adopted to achieve the coupling solution of velocity and pressure. The computational results shows that there is great flow impact on the head of vanes at different working conditions, and there is great flow separation at the tailing of the guide vanes at different working conditions, and all will affect the performance of pump. Based on the computational results, optimizations were carried out to decrease the impact on the head of vanes and flow separation at the tailing of the guide vanes. The optimized model was simulated and its performance was predicted. The computational results show that the impact on the head of vanes and the separation at the tailing of the guide vanes disappeared. The high efficiency of the optimized pump is wide, and it fit the original design destination. The newly designed mixed flow pump is now in modeling and its experimental performance will be getting soon.

  12. Laser Anemometer Measurements of the Flow Field in a 4:1 Pressure Ratio Centrifugal Impeller

    Science.gov (United States)

    Skoch, G. J.; Prahst, P. S.; Wernet, M. P.; Wood, J. R.; Strazisar, A. J.

    1997-01-01

    A laser-doppler anemometer was used to obtain flow-field velocity measurements in a 4:1 pressure ratio, 4.54 kg/s (10 lbm/s), centrifugal impeller, with splitter blades and backsweep, which was configured with a vaneless diffuser. Measured through-flow velocities are reported for ten quasi-orthogonal survey planes at locations ranging from 1% to 99% of main blade chord. Measured through-flow velocities are compared to those predicted by a 3-D viscous steady flow analysis (Dawes) code. The measurements show the development and progression through the impeller and vaneless diffuser of a through-flow velocity deficit which results from the tip clearance flow and accumulation of low momentum fluid centrifuged from the blade and hub surfaces. Flow traces from the CFD analysis show the origin of this deficit which begins to grow in the inlet region of the impeller where it is first detected near the suction surface side of the passage. It then moves toward the pressure side of the channel, due to the movement of tip clearance flow across the impeller passage, where it is cut by the splitter blade leading edge. As blade loading increases toward the rear of the channel the deficit region is driven back toward the suction surface by the cross-passage pressure gradient. There is no evidence of a large wake region that might result from flow separation and the impeller efficiency is relatively high. The flow field in this impeller is quite similar to that documented previously by NASA Lewis in a large low-speed backswept impeller.

  13. Modeling Air Bubble Transport in Hydraulic Jump Flows using Population Balance Approach

    Directory of Open Access Journals (Sweden)

    Min Xiang

    2016-01-01

    Full Text Available This paper proposed a numerical model aiming at coupling the MUltiple-SIze-Group (MUSIG with the semiempirical air entrainment model based on the Euler-Euler two-fluid framework to handle the bubble transport in hydraulic jump flows. The internal flow structure including the recirculation region, the shear layer region and the jet region was accurately predicted. The flow parameters such as the water velocity and void fraction distributions were examined and compared with the experimental data, validating the effectiveness of the numerical model. Prediction of the Sauter mean bubble diameter distributions by the population balance approach at different axial locations confirmed the dominance of breakage due to the high turbulent intensity in the shear layer region which led to the generation of small gas bubbles at high void fraction. Comparison between different cases indicates that high Froude number not only give rise to longer recirculation region and higher void fraction due to larger air entrainment rate, but also generate larger bubble number density and smaller bubble size because of the stronger turbulence intensity in the same axial position.

  14. Stability of optimal streaks in the buffer layer of a turbulent channel flow with variable viscosity

    Science.gov (United States)

    Patel, Ashish; Rinaldi, Enrico; Pecnik, Rene; Schlatter, Philipp; Bagheri, Shervin

    2016-11-01

    Direct Numerical Simulations (DNS) of turbulent channel flows with variable viscosity (Patel et al., 2015, PoF) show that low speed streaks in the buffer layer strengthen and are stabilized for increasing viscosity away from the wall, as they do not lift and tilt as intensely as in a constant property flow. The opposite holds for cases where viscosity decreases away from the wall. In this work, we investigate the above observation by studying the linear stability of the mean turbulent velocity profile obtained from DNS of variable viscosity flows. Examples of such studies for constant property turbulent flows include work of del Alamo & Jiménez, 2006, JFM and Pujals et al., 2009, PoF. The calculated optimal buffer layer streaks show larger transient energy growth for a case where the viscosity increases away from the wall. We further study the stability of the saturated optimal streaks by imposing a secondary sinuous perturbation and by following the nonlinear evolution of the structures in time. The present investigation will improve the understanding of the near-wall turbulence cycle for wall-bounded turbulent flows with viscosity gradients.

  15. Vortex propagation around a wall-mounted obstacle in pulsatile flow

    Science.gov (United States)

    Carr, Ian A.; Plesniak, Michael W.

    2015-11-01

    Wall-mounted obstacles are prevalent in nature and engineering applications. Physiological flows observed in human vocal fold pathologies, such as polyps, can be modeled by flow over a wall-mounted protuberance. Despite their prevalence, studies of wall-mounted obstacles have been restricted to steady (constant velocity) freestream flow. In biological and geophysical applications, pulsatile flow is much more common, yet effects of pulsatility on the wake of a wall-mounted obstacle remain to be extensively studied. This study aims to characterize the complex physics produced in this unsteady, separated flow. Experiments were performed in a low-speed wind tunnel with a set of rotating vanes, which produce the pulsatile inflow waveform. Instantaneous and phase-averaged particle image velocimetry (PIV) results acquired around a hemispherical obstacle are presented and compared. A mechanism based on self-induced vortex propagation, analogous to that in vortex rings, is proposed to explain the observed dynamics of coherent structures. Predictions of the propagation velocity based on analytical expressions for vortex rings in a viscous fluid are compared to the experimentally measured propagation velocity. Effects of the unsteady boundary layer on the observed physics are explored. This material is based in part upon work supported by the National Science Foundation under Grant Number CBET-1236351, and GW Center for Biomimetics and Bioinspired Engineering (COBRE).

  16. Flow separation control on swept wing with nanosecond pulse driven DBD plasma actuators

    Directory of Open Access Journals (Sweden)

    Zhao Guangyin

    2015-04-01

    Full Text Available A 15° swept wing with dielectric barrier discharge plasma actuator is designed. Experimental study of flow separation control with nanosecond pulsed plasma actuation is performed at flow velocity up to 40 m/s. The effects of the actuation frequency and voltage on the aerodynamic performance of the swept wing are evaluated by the balanced force and pressure measurements in the wind tunnel. At last, the performances on separation flow control of the three types of actuators with plane and saw-toothed exposed electrodes are compared. The optimal actuation frequency for the flow separation control on the swept wing is detected, namely the reduced frequency is 0.775, which is different from 2-D airfoil separation control. There exists a threshold voltage for the low swept wing flow control. Before the threshold voltage, as the actuation voltage increases, the control effects become better. The maximum lift is increased by 23.1% with the drag decreased by 22.4% at 14°, compared with the base line. However, the best effects are obtained on actuator with plane exposed electrode in the low-speed experiment and the abilities of saw-toothed actuators are expected to be verified under high-speed conditions.

  17. Inception mechanism and suppression of rotating stall in an axial-flow fan

    Science.gov (United States)

    Nishioka, T.

    2013-12-01

    Inception patterns of rotating stall at two stagger-angle settings for the highly loaded rotor blades were experimentally investigated in a low-speed axial-flow fan. Rotor-tip flow fields were also numerically investigated to clarify the mechanism behind the rotating stall inception. The stall inception patterns depended on the rotor stagger-angle settings. The stall inception from a rotating instability was confirmed at the design stagger-angle settings. The stall inception from a short length-scale stall cell (spike) was also confirmed at the small stagger-angle setting. The spillage of tip-leakage flow and the tip-leakage vortex breakdown influence the rotating stall inception. An air-separator has been developed based on the clarified inception mechanism of rotating stall. The rotating stall was suppressed by the developed air-separator, and the operating range of fan was extended towards low flow rate. The effect of developed air-separator was also confirmed by application to a primary air fan used in a coal fired power plant. It is concluded from these results that the developed air-separator can provide a wide operating range for an axial-flow fan.

  18. Edge states as mediators of bypass transition in boundary-layer flows

    CERN Document Server

    Khapko, Taras; Schlatter, Philipp; Duguet, Yohann; Eckhardt, Bruno; Henningson, Dan S

    2016-01-01

    The concept of edge state is investigated in the asymptotic suction boundary layer in relation with the receptivity process to noisy perturbations and the nucleation of turbulent spots. Edge tracking is first performed numerically, without imposing any discrete symmetry, in a large computational domain allowing for full spatial localisation of the perturbation velocity. The edge state is a three-dimensional localised structure recurrently characterised by a single low-speed streak that experiences erratic bursts and planar shifts. This recurrent streaky structure is then compared with predecessors of individual spot nucleation events, triggered by non-localised initial noise. The present results suggest a nonlinear picture, rooted in dynamical systems theory, of the nucleation process of turbulent spots in boundary-layer flows, in which the localised edge state play the role of state-space mediator.

  19. Edge states as mediators of bypass transition in boundary-layer flows

    Science.gov (United States)

    Khapko, T.; Kreilos, T.; Schlatter, P.; Duguet, Y.; Eckhardt, B.; Henningson, D. S.

    2016-08-01

    The concept of edge state is investigated in the asymptotic suction boundary layer in relation with the receptivity process to noisy perturbations and the nucleation of turbulent spots. Edge tracking is first performed numerically, without imposing any discrete symmetry, in a large computational domain allowing for full spatial localisation of the perturbation velocity. The edge state is a three-dimensional localised structure recurrently characterised by a single low-speed streak that experiences erratic bursts and planar shifts. This recurrent streaky structure is then compared with predecessors of individual spot nucleation events, triggered by non-localised initial noise. The present results suggest a nonlinear picture, rooted in dynamical systems theory, of the nucleation process of turbulent spots in boundary-layer flows, in which the localised edge state play the role of state-space mediator.

  20. Phase-locked stereoscopic PIV measurements of the turbulent swirling flow in a dynamic model of a uniflow-scavenged two-stroke engine cylinder

    DEFF Research Database (Denmark)

    Ingvorsen, Kristian Mark; Meyer, Knud Erik; Walther, Jens Honore

    2013-01-01

    turbulence models. In the present work, the flow in a dynamic scale model of a uniflow-scavenged cylinder is investigated experimentally. The model has a transparent cylinder and a movable piston driven by a linear motor. The flow is investigated using phase-locked stereoscopic particle image velocimetry......It is desirable to use computational fluid dynamics for the optimization of in-cylinder processes in large two-stroke low-speed uniflowscavenged marine diesel engines. However, the complex nature of the turbulent swirling in-cylinder flow necessitates experimental data for validation of the used...... (PIV) and time resolved laser Doppler anemometry (LDA). Radial profiles of the phase-averaged mean velocities are computed from the velocity fields recorded with PIV and the validity of the obtained profiles is demonstrated by comparison with reference LDA measurements. Radial profiles are measured...

  1. Conditional moment closure for two-phase flows - A review of recent developments and application to various spray combustion configurations

    Science.gov (United States)

    Wright, Y. M.; Bolla, M.; Boulouchos, K.; Borghesi, G.; Mastorakos, E.

    2015-01-01

    Energy conversion devices of practical interest such as engines or combustors operate in highly turbulent flow regimes. Due to the nature of the hydrocarbon fuels employed, the oxidation chemistry involves a broad range of time-scales some of which cannot be decoupled from the flow. Among the approaches utilised to tackle the modelling of turbulent combustion, Conditional Moment Closure (CMC), belonging to the computationally efficient class of presumed PDF methods, has shown great potential. For single-phase flows it has been demonstrated on non-premixed turbulent lifted and opposed jets, lifted flames and auto-igniting jets. Here we seek to review recent advances in both modelling and application of CMC for auto-ignition of fuel sprays. The experiments chosen for code validation and model improvement include generic spray test rigs with dimensions of passenger car as well as large two-stroke marine engines. Data for a broad range of operating conditions of a heavy-duty truck engine is additionally employed to assess the predictive capability of the model with respect to NOx emissions. An outlook on future enhancements including e.g. LES-CMC formulation also for two-phase flows as well as developments in the field of soot emissions are summarised briefly.

  2. Ultrasonic flow meter

    NARCIS (Netherlands)

    Lötters, Joost Conrad; Snijders, G.J.; Volker, A.W.F.

    2014-01-01

    The invention relates to an ultrasonic flow meter comprising a flow tube for the fluid whose flow rate is to be determined. The flow meter comprises a transmitting element for emitting ultrasonic waves, which is provided on the outer jacket of the flow tube. A receiving element, which is provided on

  3. Direct numerical simulation of Taylor-Couette flow subjected to a radial temperature gradient

    Energy Technology Data Exchange (ETDEWEB)

    Teng, Hao; Liu, Nansheng, E-mail: lns@ustc.edu.cn; Lu, Xiyun [Department of Modern Mechanics, University of Science and Technology of China, Hefei, Anhui 230026 (China); Khomami, Bamin, E-mail: bkhomami@utk.edu [Department of Chemical and Biomolecular Engineering, The University of Tennessee, Knoxville, Tennessee 37996 (United States)

    2015-12-15

    Direct numerical simulations have been performed to study the Taylor-Couette (TC) flow between two rotating, coaxial cylinders in the presence of a radial temperature gradient. Specifically, the influence of the buoyant force and the outer cylinder rotation on the turbulent TC flow system with the radius ratio η = 0.912 was examined. For the co-rotating TC flows with Re{sub i} (inner cylinder) =1000 and Re{sub o} (outer cylinder) =100, a transition pathway to highly turbulent flows is realized by increasing σ, a parameter signifying the ratio of buoyant to inertial force. This nonlinear flow transition involves four intriguing states that emerge in sequence as chaotic wavy vortex flow for σ = 0, wavy interpenetrating spiral flows for σ = 0.02 and 0.05, intermittent turbulent spirals for σ = 0.1 and 0.2, and turbulent spirals for σ = 0.4. Overall, the fluid motion changes from a centrifugally driven flow regime characterized by large-scale wavy Taylor vortices (TVs) to a buoyancy-dominated flow regime characterized by small-scale turbulent vortices. Commensurate changes in turbulence statistics and heat transfer are seen as a result of the weakening of large-scale TV circulations and enhancement of turbulent motions. Additionally, the influence of variation of the outer cylinder rotation, −500 < Re{sub o} < 500 in presence of buoyancy (σ = 0.1) with Re{sub i} = 1000, has been considered. Specifically, it is demonstrated that this variation strongly influences the azimuthal and axial mean flows with a weaker influence on the fluctuating fluid motions. Of special interest, here are the turbulent dynamics near the outer wall where a marked decrease of turbulence intensity and a sign inversion of the Reynolds stress R{sub rz} are observed for the strongly counter-rotating regimes (Re{sub o} = − 300 and −500). To this end, it has been shown that the underlying flow physics for this drastic modification are associated with the modification of the correlation

  4. Low Reynolds number flow in rectangular cooling channels provided with low aspect ratio pin fins

    Energy Technology Data Exchange (ETDEWEB)

    Armellini, Alessandro; Casarsa, Luca [Dipartimento di Energetica e Macchine, Universita di Udine, Via delle Scienze 208, 33100 Udine (Italy); Giannattasio, Pietro, E-mail: pietro.giannattasio@uniud.i [Dipartimento di Energetica e Macchine, Universita di Udine, Via delle Scienze 208, 33100 Udine (Italy)

    2010-08-15

    The flow structures around single heat transfer promoters of different shapes (square, circular, triangular and rhomboidal) have been investigated experimentally by means of a 2-D Particle Image Velocimetry (PIV) technique. The geometrical configuration and flow conditions considered are typical of real liquid cooling channels. They include low aspect ratio pin fins confined at both ends by the walls of a rectangular channel, water flow at low Reynolds numbers (Re = 800, 1800, 2800), high core flow turbulence and undeveloped boundary layers at the position of the obstacle. In front of the pin fins the high turbulence level is found to promote a strong instability of the horseshoe vortex system that forms at the wall/obstacle junction. In particular, frequent events of break-away of the primary vortices and inrush of core fluid, which are known to enhance the wall heat transfer, are observed in the cases of square and circular pins already from Re = 1800. The near wake downstream of the obstacles appears to be influenced by streamwise oriented vortical structures produced at the wall/obstacle junction. They give rise to spanwise velocity components (up-wash flow) that lead to a three-dimensional mass recirculation behind the pins. The combination of up-wash flows, low Reynolds number and high core flow turbulence gives rise to a competition between the classical alternate vortex shedding and an irregular shedding mode characterized by the decoupling of the shear layers and the absence of well organized primary structures. At Re = 800, the irregular shedding prevails and the mean wake topology is almost insensitive to the obstacle shape. As the Reynolds number is increased, the junction flow structures reduce in size and strength, their effect on the wake flow weakens and the recirculation structures behind the obstacles differentiate significantly according to the pin shape. Besides investigating complex flow structures in geometrical and flow configurations of

  5. Influence of SPS casing treatment on axial flow compressor subjected to radial pressure distortion

    Directory of Open Access Journals (Sweden)

    Fanyu Li

    2017-04-01

    Full Text Available The present work is about the stall margin enhancement ability of a kind of stall precursor-suppressed (SPS casing treatment when fan/compressor suffers from a radial total pressure inlet distortion. Experimental researches are conducted on a low-speed compressor with and without SPS casing treatment under radial distorted inlet flow of different levels as well as uniform inlet flow. The distorted flow fields of different levels are generated by annular distortion flow generators of different heights. The characteristic curves under these conditions are measured and analyzed. The results show that the radial inlet distortion could cause a stall margin loss from 2% to 30% under different distorted levels. The SPS casing treatment could remedy this stall margin loss under small distortion level and only partly make up the stall margin loss caused by distortion in large level without leading to perceptible additional efficiency loss and obvious change of characteristic curves. The pre-stall behavior of the compressor is investigated to reveal the mechanism of this stall margin improvement ability of the SPS casing treatment. The results do show that this casing treatment delays the occurrence of rotating stall by weakening the pressure perturbations and suppressing the nonlinear amplification of the stall precursor waves in the compression system.

  6. Implicit unified gas-kinetic scheme for steady state solutions in all flow regimes

    Science.gov (United States)

    Zhu, Yajun; Zhong, Chengwen; Xu, Kun

    2016-06-01

    This paper presents an implicit unified gas-kinetic scheme (UGKS) for non-equilibrium steady state flow computation. The UGKS is a direct modeling method for flow simulation in all regimes with the updates of both macroscopic flow variables and microscopic gas distribution function. By solving the macroscopic equations implicitly, a predicted equilibrium state can be obtained first through iterations. With the newly predicted equilibrium state, the evolution equation of the gas distribution function and the corresponding collision term can be discretized in a fully implicit way for fast convergence through iterations as well. The lower-upper symmetric Gauss-Seidel (LU-SGS) factorization method is implemented to solve both macroscopic and microscopic equations, which improves the efficiency of the scheme. Since the UGKS is a direct modeling method and its physical solution depends on the mesh resolution and the local time step, a physical time step needs to be fixed before using an implicit iterative technique with a pseudo-time marching step. Therefore, the physical time step in the current implicit scheme is determined by the same way as that in the explicit UGKS for capturing the physical solution in all flow regimes, but the convergence to a steady state speeds up through the adoption of a numerical time step with large CFL number. Many numerical test cases in different flow regimes from low speed to hypersonic ones, such as the Couette flow, cavity flow, and the flow passing over a cylinder, are computed to validate the current implicit method. The overall efficiency of the implicit UGKS can be improved by one or two orders of magnitude in comparison with the explicit one.

  7. Gas flow measurement using laminar flow elements

    Energy Technology Data Exchange (ETDEWEB)

    Weigand, J. [Meriam Instrument, Cleveland, OH (United States)

    1994-12-31

    An instrument that measures gas volumetric flow rate using a capillary tube laminar-flow principle is described. Irs construction, operation, accuracy, and rangeability are presented. Discussion includes integrating the differential-pressure-producing flowmeter with appropriate temperature find pressure devices to produce a digital flowmeter system capable of measuring volumetric and mass flow rates. Typical applications are described.

  8. Flow of Aqueous Humor

    Science.gov (United States)

    ... Home Flow of Aqueous Humor Flow of Aqueous Humor Most, but not all, forms of glaucoma are ... remains normal when some of the fluid (aqueous humor) produced by the eye's ciliary body flows out ...

  9. Theoretical analysis of the flow around a Savonius rotor

    Energy Technology Data Exchange (ETDEWEB)

    Aouachria, Z.; Djoumati, D. [Batna Univ., Batna (Algeria). Laboratoire de Physique Energetique Appliquee; Djamel, H. [Batna Univ., Batna (Algeria). Dept. de Mecanique Energetique

    2009-07-01

    While Savonius rotors do not perform as well as Darrieus wind turbine rotors, Savonius rotors work in all wind directions, do not require a rudder, and are capable of operating at relatively low speeds. A discrete vortex method was used to analyze the complex flow around a Savonius rotor. Velocity and pressure fields obtained in the analysis were used to determine both mechanical and energetic rotor performance. Savonius rotor bi-blades were considered in relation to 4 free eddies, the leakage points of each blade, and the distribution of basic eddies along the blades. Each blade was divided into equal elementary arcs. Linear equations and Kelvin theorem were reduced to a single equation. Results showed good agreement with data obtained in previous experimental studies. The study demonstrated that vortice emissions were unbalanced. The resistant blade had 2 vortice emissions, while the driving blade had only a single vortex. The results of the study will be used to clarify the mechanical and aerodynamic functions as well as to determine the different values between the blades and the speed of the turbine's engine. 9 refs., 4 figs.

  10. Optimal Power Flow with Power Flow Routers

    OpenAIRE

    2016-01-01

    Power flow routing is an emerging control paradigm for the dynamic control of electric power flows. In this paper, we propose a generic model of a power flow router (PFR) and incorporate it into the optimal power flow (OPF) problem. First, a generic PFR architecture is proposed to encapsulate the desired functions of PFRs. Then, the load flow model of PFRs is developed and incorporated into the OPF framework. To pursue global optimality of the non-convex PFR-incorporated OPF (PFR-OPF) problem...

  11. An investigational study of minimum rotational pump speed to avoid retrograde flow in three centrifugal blood pumps in a pediatric extracorporeal life support model.

    Science.gov (United States)

    Clark, Joseph B; Guan, Yulong; McCoach, Robert; Kunselman, Allen R; Myers, John L; Undar, Akif

    2011-05-01

    During extracorporeal life support with centrifugal blood pumps, retrograde pump flow may occur when the pump revolutions decrease below a critical value determined by the circuit resistance and the characteristics of the pump. We created a laboratory model to evaluate the occurrence of retrograde flow in each of three centrifugal blood pumps: the Rotaflow, the CentriMag, and the Bio-Medicus BP-50. At simulated patient pressures of 60, 80, and 100 mmHg, each pump was evaluated at speeds from 1000 to 2200 rpm and flow rates were measured. Retrograde flow occurred at low revolution speeds in all three centrifugal pumps. The Bio-Medicus pump was the least likely to demonstrate retrograde flow at low speeds, followed by the Rotaflow pump. The CentriMag pump showed the earliest transition to retrograde flow, as well as the highest degree of retrograde flow. At every pump speed evaluated, the Bio-Medicus pump delivered the highest antegrade flow and the CentriMag pump delivered the least.

  12. Simulation of Flow Pattern around Inclined Bridge Group Pier using FLOW-3D Software

    Directory of Open Access Journals (Sweden)

    Malihesadat Jafari

    2017-03-01

    around the piers group is entirely different than that for a single pier and consequently the outcomes of the flow pattern around single pier cannot be generalized to the pier group. At all levels of foundation setting, longitudinal component of flow velocity increases surrounding the first pier. The increase in the area and its extension towards downstream is caused by the constriction the flow due to the pier and area rotating of the wake vortex in downstream. When the pier foundation is set at the stream bed, the bed rotating flows extend to a distance between the two piers from near the bed up to the middle of flow depth while in upstream of the second pier and near water surface, the stream lines become parallel to the bed. The comparison of the results of the changes in bed shear stress in the situations of foundation setting in different levels showed that the maximum shear stress occurred when the foundation level is at the bed level and the maximum shear stress exerted on the bed decreases by factors of 17% and 53% in the cases of foundation level to be below and above bed levels, respectively. In addition, the results showed that, the amount of vortex flows increased in upstream piers group and near bed in the case of setting the foundation above the bed. This is because of the fact that the volume of piers group acted as obstacle against flow was more than other level settings. Furthermore, based on the obtained results, in the case of foundation level is set at the bed, the quantity and development zone of vortex flow are much higher than those observed when the setting foundation is below the bed level. This can be attributed to the higher effect of the second pier on the flow pattern being between the first and the second piers. Stream lines turn downward in the range between piers group, and after the collision to bed turn upward to water surface and cause to form rotating flow and hence high turbulence intensity in the area. In the near water surface and

  13. Flow Distances on Open Flow Networks

    CERN Document Server

    Guo, Liangzhu; Shi, Peiteng; Wang, Jun; Huang, Xiaohan; Zhang, Jiang

    2015-01-01

    Open flow network is a weighted directed graph with a source and a sink, depicting flux distributions on networks in the steady state of an open flow system. Energetic food webs, economic input-output networks, and international trade networks, are open flow network models of energy flows between species, money or value flows between industrial sectors, and goods flows between countries, respectively. Flow distances (first-passage or total) between any given two nodes $i$ and $j$ are defined as the average number of transition steps of a random walker along the network from $i$ to $j$ under some conditions. They apparently deviate from the conventional random walk distance on a closed directed graph because they consider the openness of the flow network. Flow distances are explicitly expressed by underlying Markov matrix of a flow system in this paper. With this novel theoretical conception, we can visualize open flow networks, calculating centrality of each node, and clustering nodes into groups. We apply fl...

  14. Estudio histológico comparativo de la reparación ósea entre hueso alveolar y extra-alveolar en los cerdos sometidos a osteotomía con alta y baja velocidad, con refrigeración líquida Comparative study of bone repair between alveolar and extra-alveolar bone in pigs subjected to osteotomy at low speed and high speed with liquid refrigeration

    Directory of Open Access Journals (Sweden)

    Henrique José Baldo de Toledo

    2012-03-01

    models, the present study has as its aim to evaluate the histological bone repair process of osteotomy performed on alveolar and extra-alveolar bones, using drilling tools with liquid refrigeration. Material and method Eighteen Large White pigs weighing between 20 and 25 Kg were divided into three groups of six animals in order to evaluate the osteotomy repairs with low and high speed in the alveolar bone and threes in the extra-alveolar area, study periods of 7, 14 and 28 days. Results: It was observed that in the alveolar bone at the postoperative times of 14 and 28 days, the best repair results were in the osteotomy performed with low speed, while in the 7 day postoperative period, the results with high speed were slightly better, in alveolar areas as well as extra-alveolar areas. There no statistically significant differences between the alveolar and extra-alveolar bone repair process. Conclusions: The repair process, by means of microscopic analysis in the alveolar and extra-alveolar areas, are similar with better results observed in osteotomies performed with low speed drills in the 14 and 28 day study periods, and at 7 days postoperative the results with high speed drills and refrigeration were slightly better. Research works using pigs as an animal model are perfectly viable.

  15. Radiation-transport method to simulate noncontinuum gas flows for MEMS devices.

    Energy Technology Data Exchange (ETDEWEB)

    Gallis, Michail A.; Torczynski, John Robert

    2004-01-01

    A Micro Electro Mechanical System (MEMS) typically consists of micron-scale parts that move through a gas at atmospheric or reduced pressure. In this situation, the gas-molecule mean free path is comparable to the geometric features of the microsystem, so the gas flow is noncontinuum. When mean-free-path effects cannot be neglected, the Boltzmann equation must be used to describe the gas flow. Solution of the Boltzmann equation is difficult even for the simplest case because of its sevenfold dimensionality (one temporal dimension, three spatial dimensions, and three velocity dimensions) and because of the integral nature of the collision term. The Direct Simulation Monte Carlo (DSMC) method is the method of choice to simulate high-speed noncontinuum flows. However, since DSMC uses computational molecules to represent the gas, the inherent statistical noise must be minimized by sampling large numbers of molecules. Since typical microsystem velocities are low (< 1 m/s) compared to molecular velocities ({approx}400 m/s), the number of molecular samples required to achieve 1% precision can exceed 1010 per cell. The Discrete Velocity Gas (DVG) method, an approach motivated by radiation transport, provides another way to simulate noncontinuum gas flows. Unlike DSMC, the DVG method restricts molecular velocities to have only certain discrete values. The transport of the number density of a velocity state is governed by a discrete Boltzmann equation that has one temporal dimension and three spatial dimensions and a polynomial collision term. Specification and implementation of DVG models are discussed, and DVG models are applied to Couette flow and to Fourier flow. While the DVG results for these benchmark problems are qualitatively correct, the errors in the shear stress and the heat flux can be order-unity even for DVG models with 88 velocity states. It is concluded that the DVG method, as described herein, is not sufficiently accurate to simulate the low-speed gas flows

  16. PIV experiment of flow field in sewage pump with forward-extended double blades%前伸式双叶片污水泵内部流场PIV试验

    Institute of Scientific and Technical Information of China (English)

    郎涛; 施卫东; 陈刻强; 李伟; 张德胜

    2015-01-01

    The back-swept double blades sewage pump studied in the paper belongs to the new high efficiency non clogging pump. It has the self-cleaning ability and can effectively solve the problem of fiber winding and congestion. This research was taken on probing the internal flow pattern of relative velocity flow field in the back-swept double blades sewage pump, of which the specific speed was 70. The main design parameters of the pump showed as follows: design flow rateQdes=17 m3/h, headH=9 m, rotation speedn=1 450 r/min. Performance test was done to get the performance parameters curves and results showed the highest efficiency is 61.9% whenQ=21.1 m3/h, corresponding to H=8.2 m. Then PIV test was done and the field distribution for relative velocity flow in the impeller was got. The test PIV system was the US TSI company's commercial PIV system, including: YAG200-NWL type pulse laser; 610035-type synchronizer; 630059POWERVIEW 4MP type cross-frame CCD camera; embedded Tecplot software for image acquisition and data analysis systems Insight 3G; 610015-SOL type light arms and light sheet lens group. External trigger synchronization system comprising: a shaft encoders, flexible couplings, synchronous trigger controller and optical fiber transmission converter. By analyzing the distribution of relative velocity of the impeller in different flow rate conditions (Q/Qdes=0.4, 0.6, 0.8, 1, 1.2, 1.4), we found the variation of axial vortexes and low-speed zones in the impeller. When the flow rate changes from small to large, low-speed zones decrease, and the axial vortex zones were also reduced. When the flow rate changed fromQ/Qdes=0.4 toQ/Qdes=0.6 which means the test the pump was at low flow rate conditions, there were large low-speed regions, axial vortex zones, and the flow field was very unstable, which meaned large hydraulic losses. These axial vortices scattered pressure sides of blades near the inlet, and spreaded to the back of the blade. When the flow rate changes from

  17. Water Tank Experiments on Stratified Flow over Double Mountain-Shaped Obstacles at High-Reynolds Number

    Directory of Open Access Journals (Sweden)

    Ivana Stiperski

    2017-01-01

    Full Text Available In this article, we present an overview of the HyIV-CNRS-SecORo (Hydralab IV-CNRS-Secondary Orography and Rotors Experiments laboratory experiments carried out in the CNRM (Centre National de Recherches Météorologiques large stratified water flume. The experiments were designed to systematically study the influence of double obstacles on stably stratified flow. The experimental set-up consists of a two-layer flow in the water tank, with a lower neutral and an upper stable layer separated by a sharp density discontinuity. This type of layering over terrain is known to be conducive to a variety of possible responses in the atmosphere, from hydraulic jumps to lee waves and highly turbulent rotors. In each experiment, obstacles were towed through the tank at a constant speed. The towing speed and the size of the tank allowed high Reynolds-number flow similar to the atmosphere. Here, we present the experimental design, together with an overview of laboratory experiments conducted and their results. We develop a regime diagram for flow over single and double obstacles and examine the parameter space where the secondary obstacle has the largest influence on the flow. Trapped lee waves, rotors, hydraulic jumps, lee-wave interference and flushing of the valley atmosphere are successfully reproduced in the stratified water tank. Obstacle height and ridge separation distance are shown to control lee-wave interference. Results, however, differ partially from previous findings on the flow over double ridges reported in the literature due to the presence of nonlinearities and possible differences in the boundary layer structure. The secondary obstacle also influences the transition between different flow regimes and makes trapped lee waves possible for higher Froude numbers than expected for an isolated obstacle.

  18. Evolution and Flow.

    Science.gov (United States)

    Csikszentmihalyi, Mihaly

    1997-01-01

    Presents flow theory in the context of evolution. Defines the elements of "flow" and contends that flow results in an optimal state of inner harmony which improves one's chance for survival. Identifies consequences of flow for creativity, peak performance, talent development, productivity, self-esteem, and stress reduction. Examines the…

  19. The flow over a thin airfoil subjected to elevated levels of freestream turbulence at low Reynolds numbers

    Science.gov (United States)

    Ravi, Sridhar; Watkins, Simon; Watmuff, Jon; Massey, Kevin; Petersen, Phred; Marino, Matthew; Ravi, Anuradha

    2012-09-01

    Micro Air Vehicles (MAVs) can be difficult to control in the outdoor environment as they fly at relatively low speeds and are of low mass, yet exposed to high levels of freestream turbulence present within the Atmospheric Boundary Layer. In order to examine transient flow phenomena, two turbulence conditions of nominally the same longitudinal integral length scale (Lxx/c = 1) but with significantly different intensities (Ti = 7.2 % and 12.3 %) were generated within a wind tunnel; time-varying surface pressure measurements, smoke flow visualization, and wake velocity measurements were made on a thin flat plate airfoil. Rapid changes in oncoming flow pitch angle resulted in the shear layer to separate from the leading edge of the airfoil even at lower geometric angles of attack. At higher geometric angles of attack, massive flow separation occurred at the leading edge followed by enhanced roll up of the shear layer. This lead to the formation of large Leading Edge Vortices (LEVs) that advected at a rate much lower than the mean flow speed while imparting high pressure fluctuations over the airfoil. The rate of LEV formation was dependent on the angle of attack until 10° and it was independent of the turbulence properties tested. The fluctuations in surface pressures and consequently aerodynamic loads were considerably limited on the airfoil bottom surface due to the favorable pressure gradient.

  20. Wall interference in a two-dimensional-flow wind tunnel, with consideration of the effect of compressibility

    Science.gov (United States)

    Allen, H Julian; Vincenti, Walter G

    1944-01-01

    Theoretical tunnel-wall corrections are derived for an airfoil of finite thickness and camber in a two-dimensional-flow wind tunnel. The theory takes account of the effects of the wake of the airfoil and of the compressibility of the fluid, and is based upon the assumption that the chord of the airfoil is small in comparison with the height of the tunnel. Consideration is given to the phenomenon of choking at high speeds and its relation to the tunnel-wall corrections. The theoretical results are compared with the small amount of low-speed experimental data available and the agreement is seen to be satisfactory, even for relatively large values of the chord-height ratio.

  1. Thermal flow micro sensors

    OpenAIRE

    Elwenspoek, M.

    1999-01-01

    A review is given on sensors fabricated by silicon micromachining technology using the thermal domain for the measurement of fluid flow. Attention is paid especially to performance and geometry of the sensors. Three basic types of thermal flow sensors are discussed: anemometers, calorimetric flow sensors and time of flight flow sensors. Anemometers may comprise several heaters and temperature sensors and from a geometric point of view are similar sometimes for calorimetric flow sensors. We fi...

  2. [Design Method Analysis and Performance Comparison of Wall Filter for Ultrasound Color Flow Imaging].

    Science.gov (United States)

    Wang, Lutao; Xiao, Jun; Chai, Hua

    2015-08-01

    The successful suppression of clutter arising from stationary or slowly moving tissue is one of the key issues in medical ultrasound color blood imaging. Remaining clutter may cause bias in the mean blood frequency estimation and results in a potentially misleading description of blood-flow. In this paper, based on the principle of general wall-filter, the design process of three classes of filters, infinitely impulse response with projection initialization (Prj-IIR), polynomials regression (Pol-Reg), and eigen-based filters are previewed and analyzed. The performance of the filters was assessed by calculating the bias and variance of a mean blood velocity using a standard autocorrelation estimator. Simulation results show that the performance of Pol-Reg filter is similar to Prj-IIR filters. Both of them can offer accurate estimation of mean blood flow speed under steady clutter conditions, and the clutter rejection ability can be enhanced by increasing the ensemble size of Doppler vector. Eigen-based filters can effectively remove the non-stationary clutter component, and further improve the estimation accuracy for low speed blood flow signals. There is also no significant increase in computation complexity for eigen-based filters when the ensemble size is less than 10.

  3. A semi-Lagrangian gas-kinetic scheme for smooth flows

    CERN Document Server

    Wang, Peng

    2014-01-01

    In this paper, a semi-Lagrangian gas-kinetic scheme is developed for smooth flows based on the Bhatnagar-Gross-Krook (BGK) equation. As a finite-volume scheme, the evolution of the average flow variables in a control volume is under the Eulerian framework, whereas the construction of the numerical flux across the cell interface comes from the Lagrangian perspective. The adoption of the Lagrangian aspect makes the collision and the transport mechanisms intrinsically coupled together in the flux evaluation. As a result, the time step is independent of the particle collision time and solely determined by the Courant-Friedrichs-Lewy (CFL) conditions. A set of simulations are carried out to validate the performance of the new scheme. The results show that with second-order spatial accuracy, the scheme exhibits low numerical dissipation, and can accurately capture the Navier-Stokers solutions for the smooth flows with viscous heat dissipation from the low-speed incompressible to hypersonic compressible regimes.

  4. Numerical investigation of flow on NACA4412 aerofoil with different aspect ratios

    Science.gov (United States)

    Demir, Hacımurat; Özden, Mustafa; Genç, Mustafa Serdar; Çağdaş, Mücahit

    2016-03-01

    In this study, the flow over NACA4412 was investigated both numerically and experimentally at a different Reynolds numbers. The experiments were carried out in a low speed wind tunnel with various angles of attack and different Reynolds numbers (25000 and 50000). Airfoil was manufactured using 3D printer with a various aspect ratios (AR = 1 and AR = 3). Smoke-wire and oil flow visualization methods were used to visualize the surface flow patterns. NACA4412 aerofoil was designed by using SOLIDWORKS. The structural grid of numerical model was constructed by ANSYS ICEM CFD meshing software. Furthermore, ANSYS FLUENT™ software was used to perform numerical calculations. The numerical results were compared with experimental results. Bubble formation was shown in CFD streamlines and smoke-wire experiments at z / c = 0.4. Furthermore, bubble shrunk at z / c = 0.2 by reason of the effects of tip vortices in both numerical and experimental studies. Consequently, it was seen that there was a good agreement between numerical and experimental results.

  5. Discrete unified gas kinetic scheme for all Knudsen number flows: II. Compressible case

    CERN Document Server

    Guo, Zhaoli; Xu, Kun

    2014-01-01

    This paper is a continuation of our earlier work [Z.L. Guo {\\it et al.}, Phys. Rev. E {\\bf 88}, 033305 (2013)] where a multiscale numerical scheme based on kinetic model was developed for low speed isothermal flows with arbitrary Knudsen numbers. In this work, a discrete unified gas-kinetic scheme (DUGKS) for compressible flows with the consideration of heat transfer and shock discontinuity is developed based on the Shakhov model with an adjustable Prandtl number. The method is an explicit finite-volume scheme where the transport and collision processes are coupled in the evaluation of the fluxes at cell interfaces, so that the nice asymptotic preserving (AP) property is retained, such that the time step is limited only by the CFL number, the distribution function at cell interface recovers to the Chapman-Enskog one in the continuum limit while reduces to that of free-transport for free-molecular flow, and the time and spatial accuracy is of second-order accuracy in smooth region. These features make the DUGK...

  6. Parasitic Currents in Diffuse-Interface Two-Phase Flow Simulations

    Science.gov (United States)

    Milani, Pedro; Mirjalili, Seyedshahabaddin; Mani, Ali

    2016-11-01

    Two phase flow phenomena are important in a wide range of applications, such as bubble generation in ocean waves and droplet dynamics in fuel injectors. Several methods can be used to simulate such phenomena. The focus of this study is the diffuse-interface method, in which the interface is described via a mixing energy and spans a few computational cells, while surface tension is modeled as a force density term on the right-hand side of the momentum equation. The advantages of this method include the ability to easily simulate complex geometries since it does not require special treatment around the interface, and to conserve mass exactly. However, this method suffers from parasitic currents, an unphysical velocity field generated close to the interface due to numerical imprecisions in the surface tension term. This can be a serious problem in low speed flows, where the parasitic currents are significant compared to the velocity scale of the problem. In this study, we consider a wide range of diffuse-interface schemes for two-phase flows, including different options for discrete representation of the surface tension force. By presenting an assessment of each method's performance in scenarios involving parasitic currents, we develop accuracy estimates and guidelines for selection among these models. Supported by the ONR.

  7. Numerical investigation of flow on NACA4412 aerofoil with different aspect ratios

    Directory of Open Access Journals (Sweden)

    Demir Hacımurat

    2016-01-01

    Full Text Available In this study, the flow over NACA4412 was investigated both numerically and experimentally at a different Reynolds numbers. The experiments were carried out in a low speed wind tunnel with various angles of attack and different Reynolds numbers (25000 and 50000. Airfoil was manufactured using 3D printer with a various aspect ratios (AR = 1 and AR = 3. Smoke-wire and oil flow visualization methods were used to visualize the surface flow patterns. NACA4412 aerofoil was designed by using SOLIDWORKS. The structural grid of numerical model was constructed by ANSYS ICEM CFD meshing software. Furthermore, ANSYS FLUENT™ software was used to perform numerical calculations. The numerical results were compared with experimental results. Bubble formation was shown in CFD streamlines and smoke-wire experiments at z / c = 0.4. Furthermore, bubble shrunk at z / c = 0.2 by reason of the effects of tip vortices in both numerical and experimental studies. Consequently, it was seen that there was a good agreement between numerical and experimental results.

  8. Ricci flow coupled with harmonic map flow

    CERN Document Server

    Müller, Reto

    2009-01-01

    We investigate a new geometric flow which consists of a coupled system of the Ricci flow on a closed manifold M with the harmonic map flow of a map phi from M to some closed target manifold N with a (possibly time-dependent) positive coupling constant alpha. This system can be interpreted as the gradient flow of an energy functional F_alpha which is a modification of Perelman's energy F for the Ricci flow, including the Dirichlet energy for the map phi. Surprisingly, the coupled system may be less singular than the Ricci flow or the harmonic map flow alone. In particular, we can always rule out energy concentration of phi a-priori - without any assumptions on the curvature of the target manifold N - by choosing alpha large enough. Moreover, if alpha is bounded away from zero it suffices to bound the curvature of (M,g(t)) to also obtain control of phi and all its derivatives - a result which is clearly not true for alpha = 0. Besides these new phenomena, the flow shares many good properties with the Ricci flow...

  9. Study of Sweep and Induced Dihedral Effects in Subsonic Axial Flow Compressor Passages—Part I: Design Considerations—Changes in Incidence, Deflection, and Streamline Curvature

    Directory of Open Access Journals (Sweden)

    P. V. Ramakrishna

    2009-01-01

    Full Text Available This article presents the study of Tip Chordline Sweeping (TCS and Axial Sweeping (AXS of low-speed axial compressor rotor blades against the performance of baseline unswept rotor (UNS for different tip clearance levels. The first part of the paper discusses the changes in design parameters when the blades are swept, while the second part throws light on the effect of sweep on tip leakage flow-related phenomena. 15 domains are studied with 5 sweep configurations (0∘, 20∘ TCS, 30∘ TCS, 20∘ AXS, and 30∘ AXS and for 3 tip clearances (0.0%, 0.7%, and 2.7% of the blade chord. A commercial CFD package is employed for the flow simulations and analysis. Results are well validated with experimental data. Forward sweep reduced the flow incidences. This is true all over the span with axial sweeping while little higher incidences below the mid span are observed with tip chordline sweeping. Sweeping is observed to lessen the flow turning. AXS rotors demonstrated more efficient energy transfer among the rotors. Tip chordline sweep deflected the flow towards the hub while effective positive dihedral induced with axial sweeping resulted in outward deflection of flow streamlines. These deflections are more at lower mass flow rates.

  10. Numerically and Experimentally Investigated Turbulent Flow Structure Past a Single “Trench”

    Directory of Open Access Journals (Sweden)

    V. N. Afanas'ev

    2016-01-01

    Full Text Available The paper presents results of experimental and numerical investigation of hydrodynamics and heat exchange with transversal flow past a two-dimensional trench without separation. The trench is placed on the flat plate and heated according to the law of qw=const. For experimentation a subsonic low-turbulent open-type aerodynamic tunnel was used. Mean velocity and temperature profiles have been obtained experimentally in different sections of tunnel above the single transversal cylindrical trench (stream-wise size s=37.5 mm, depth h=2.5 mm, h/s=0.067 with an external flow velocity of 18 m/s. Incompressible two-dimensional RANS (Reynolds Averaged Navier-Stokes equations approach with two-parametrical k-ɛ and k-ω (MSST turbulence models has been used in ANSYS FlUENT computational research.The paper explores an impact of trench shape and geometry on the structure, turbulent boundary layer, drag friction, heat exchange and pressure on a streamlined surface.It has been shown that calculations with k-ε turbulence model constitute a match with experimental data. Thus, k-ε turbulence model should be used for the low turbulent (ɛ < 1% and low-Reynolds flow calculation and both k-ε and k- ω (MSST turbulence models could be used for the high-turbulent (ɛ > 2% flow calculations. Surface profiling with a system of transversal trenches leads to increasing heat-transfer coefficient without raising surface drag friction.The influence of different geometries of trench shapes on the heat transfer intensity has been numerically simulated. It has been revealed that in comparison with flat plate trenches with greater inlet angle have lower pressure losses and drag coefficient and substantially higher heattransfer coefficient.

  11. Characteristic analysis on the pressure fluctuation in the impeller of a low specific speed mixed flow pump

    Science.gov (United States)

    Zhang, W. W.; Yu, Z. Y.; Zhu, B. S.

    2016-05-01

    To explore the pressure fluctuation characteristics of a low speed specific speed mixed flow pump caused by rotor-stator interaction, the unsteady flow was simulated with CFX for the whole flow passage of a mixed flow pump with a specific speed of 148.8. The structured mesh of the computation domain was generated with ICEM CFD and TurboGrid, and mesh-independent analysis was done in the design condition. Through the comparison with the experiment data, the reliability of the simulation was verified. In different locations of the impeller passage, monitoring points were set. With Fast Fourier Transform (FFT), the characteristic analysis on the pressure fluctuation in the impeller passage was done for three flow rate conditions (0.75Qd, Qd, 1.25Qd). The results show that the pressure fluctuation amplitude increases from the inlet to the outlet. And the maximum values in different flow rates exist near the hub of the outlet; The pressure fluctuation is small in the design condition, but the largest in the small flow rate condition, accompanied by the secondary dominant frequencies with large amplitudes; In the small flow rate condition and design condition, the dominant frequency varies from the inlet to the outlet because the combine action of the impeller and guide vane; while in the large flow rate condition, the pressure fluctuation in the whole impeller passage is affected significantly by the guide vane, and the domain frequency is 8 times the rotational frequency of impeller. In addition, the change of pressure fluctuation from the pressure surface to the suction surface in the off-design conditions is investigated, and the results demonstrates that the intensity of the pressure fluctuation in the impeller passage is closely related with the impeller as well as the distribution of the vorticity and the pressure.

  12. Introduction to compressible fluid flow

    CERN Document Server

    Oosthuizen, Patrick H

    2013-01-01

    IntroductionThe Equations of Steady One-Dimensional Compressible FlowSome Fundamental Aspects of Compressible FlowOne-Dimensional Isentropic FlowNormal Shock WavesOblique Shock WavesExpansion Waves - Prandtl-Meyer FlowVariable Area FlowsAdiabatic Flow with FrictionFlow with Heat TransferLinearized Analysis of Two-Dimensional Compressible FlowsHypersonic and High-Temperature FlowsHigh-Temperature Gas EffectsLow-Density FlowsBibliographyAppendices

  13. Flow Element Models

    DEFF Research Database (Denmark)

    Heiselberg, Per; Nielsen, Peter V.

    Air distribution in ventilated rooms is a flow process that can be divided into different elements such as supply air jets, exhaust flows, thermal plumes, boundary layer flows, infiltration and gravity currents. These flow elements are isolated volumes where the air movement is controlled...... by a restricted number of parameters, and the air movement is fairly independent of the general flow in the enclosure. In many practical situations, the most convenient· method is to design the air distribution system using flow element theory....

  14. Unsteady flow volumes

    Energy Technology Data Exchange (ETDEWEB)

    Becker, B.G.; Lane, D.A.; Max, N.L.

    1995-03-01

    Flow volumes are extended for use in unsteady (time-dependent) flows. The resulting unsteady flow volumes are the 3 dimensional analog of streamlines. There are few examples where methods other than particle tracing have been used to visualize time varying flows. Since particle paths can become convoluted in time there are additional considerations to be made when extending any visualization technique to unsteady flows. We will present some solutions to the problems which occur in subdivision, rendering, and system design. We will apply the unsteady flow volumes to a variety of field types including moving multi-zoned curvilinear grids.

  15. Dynamic power flow controllers

    Science.gov (United States)

    Divan, Deepakraj M.; Prasai, Anish

    2017-03-07

    Dynamic power flow controllers are provided. A dynamic power flow controller may comprise a transformer and a power converter. The power converter is subject to low voltage stresses and not floated at line voltage. In addition, the power converter is rated at a fraction of the total power controlled. A dynamic power flow controller controls both the real and the reactive power flow between two AC sources having the same frequency. A dynamic power flow controller inserts a voltage with controllable magnitude and phase between two AC sources; thereby effecting control of active and reactive power flows between two AC sources.

  16. Computational Fluid Dynamics Study of Molten Steel Flow Patterns and Particle-Wall Interactions Inside a Slide-Gate Nozzle by a Hybrid Turbulent Model

    Science.gov (United States)

    Mohammadi-Ghaleni, Mahdi; Asle Zaeem, Mohsen; Smith, Jeffrey D.; O'Malley, Ronald

    2016-10-01

    Melt flow patterns and turbulence inside a slide-gate throttled submerged entry nozzle (SEN) were studied using Detached-Eddy Simulation (DES) model, which is a combination of Reynolds-Averaged Navier-Stokes (RANS) and Large-Eddy Simulation (LES) models. The DES switching criterion between RANS and LES was investigated to closely reproduce the flow structures of low and high turbulence regions similar to RANS and LES simulations, respectively. The melt flow patterns inside the nozzle were determined by k- ɛ (a RANS model), LES, and DES turbulent models, and convergence studies were performed to ensure reliability of the results. Results showed that the DES model has significant advantages over the standard k- ɛ model in transient simulations and in regions containing flow separation from the nozzle surface. Moreover, due to applying a hybrid approach, DES uses a RANS model at wall boundaries which resolves the extremely fine mesh requirement of LES simulations, and therefore it is computationally more efficient. Investigation of particle distribution inside the nozzle and particle adhesion to the nozzle wall also reveals that the DES model simulations predict more particle-wall interactions compared to LES model.

  17. A Nonideal Flow Experiment.

    Science.gov (United States)

    Gonzalez-Velasco, Juan Ramon; Elorriaga, Javier Bilbao

    1984-01-01

    Considers the deviation from the ideal flows of both a backmix tank and a backmix tank followed by a flow vessel. Background information, apparatus used, and experimental procedures are provided. Typical results are also provided and discussed. (JN)

  18. Counting RG flows

    OpenAIRE

    Gukov, Sergei

    2016-01-01

    Interpreting renormalization group flows as solitons interpolating between different fixed points, we ask various questions that are normally asked in soliton physics but not in renormalization theory. Can one count RG flows? Are there different "topological sectors" for RG flows? What is the moduli space of an RG flow, and how does it compare to familiar moduli spaces of (supersymmetric) dowain walls? Analyzing these questions in a wide variety of contexts --- from counting RG walls to AdS/C...

  19. On the dissipation and dispersion of entropy waves in heat transferring channel flows

    Science.gov (United States)

    Fattahi, A.; Hosseinalipour, S. M.; Karimi, N.

    2017-08-01

    This paper investigates the hydrodynamic and heat transfer effects on the dissipation and dispersion of entropy waves in non-reactive flows. These waves, as advected density inhomogeneities downstream of unsteady flames, may decay partially or totally before reaching the exit nozzle, where they are converted into sound. Attenuation of entropy waves dominates the significance of the subsequent acoustic noise generation. Yet, the extent of this decay process is currently a matter of contention and the pertinent mechanisms are still largely unexplored. To resolve this issue, a numerical study is carried out by compressible large eddy simulation of the wave advection in a channel subject to convective and adiabatic thermal boundary conditions. The dispersion, dissipation, and spatial correlation of the wave are evaluated by post-processing of the numerical results. This includes application of the classical coherence function as well as development of nonlinear quantitative measures of wave dissipation and dispersion. The analyses reveal that the high frequency components of the entropy wave are always strongly damped. The survival of the low frequency components heavily depends on the turbulence intensity and thermal boundary conditions of the channel. In general, high turbulence intensities and particularly heat transfer intensify the decay and destruction of the spatial coherence of entropy waves. In some cases, they can even result in the complete annihilation of the wave. The current work can therefore resolve the controversies arising over the previous studies of entropy waves with different thermal boundary conditions.

  20. Thermal flow micro sensors

    NARCIS (Netherlands)

    Elwenspoek, M.

    1999-01-01

    A review is given on sensors fabricated by silicon micromachining technology using the thermal domain for the measurement of fluid flow. Attention is paid especially to performance and geometry of the sensors. Three basic types of thermal flow sensors are discussed: anemometers, calorimetric flow se

  1. Free surface flow focusing

    NARCIS (Netherlands)

    Peters, I.R.

    2012-01-01

    Reducing the area through which a fluid is allowed to flow often leads to an increase of flow velocity. A familiar example of this is a garden hose, where one can change the rather weak stream that usually flows out into a strong jet by narrowing the orifice at the end of the hose. In this example,

  2. Integer Equal Flows

    Energy Technology Data Exchange (ETDEWEB)

    Meyers, C A; Schulz, A S

    2009-01-07

    The integer equal flow problem is an NP-hard network flow problem, in which all arcs in given sets R{sub 1}, ..., R{sub {ell}} must carry equal flow. We show this problem is effectively inapproximable, even if the cardinality of each set R{sub k} is two. When {ell} is fixed, it is solvable in polynomial time.

  3. OpenFlow cookbook

    CERN Document Server

    Smiler S, Kingston

    2015-01-01

    This book is intended for network protocol developers, SDN controller application developers, and academics who would like to understand and develop their own OpenFlow switch or OpenFlow controller in any programming language. With basic understanding of OpenFlow and its components, you will be able to follow the recipes in this book.

  4. Distributed Power Flow Controller

    NARCIS (Netherlands)

    Yuan, Z.

    2010-01-01

    In modern power systems, there is a great demand to control the power flow actively. Power flow controlling devices (PFCDs) are required for such purpose, because the power flow over the lines is the nature result of the impedance of each line. Due to the control capabilities of different types of P

  5. Free surface flow focusing

    NARCIS (Netherlands)

    Peters, I.R.

    2012-01-01

    Reducing the area through which a fluid is allowed to flow often leads to an increase of flow velocity. A familiar example of this is a garden hose, where one can change the rather weak stream that usually flows out into a strong jet by narrowing the orifice at the end of the hose. In this example,

  6. STOCHASTIC FLOWS OF MAPPINGS

    Institute of Scientific and Technical Information of China (English)

    2007-01-01

    In this paper, the stochastic flow of mappings generated by a Feller convolution semigroup on a compact metric space is studied. This kind of flow is the generalization of superprocesses of stochastic flows and stochastic diffeomorphism induced by the strong solutions of stochastic differential equations.

  7. Distributed Power Flow Controller

    NARCIS (Netherlands)

    Yuan, Z.

    2010-01-01

    In modern power systems, there is a great demand to control the power flow actively. Power flow controlling devices (PFCDs) are required for such purpose, because the power flow over the lines is the nature result of the impedance of each line. Due to the control capabilities of different types of P

  8. Flow lab.: flow visualization and simulation

    Energy Technology Data Exchange (ETDEWEB)

    Park, Chung Kyun; Cho, Won Jin; Hahn, Pil Soo [Korea Atomic Energy Research Institute, Taejeon (Korea, Republic of)

    2005-11-15

    The experimental setups for flow visualization and processes identification in laboratory scale (so called Flow Lab.) has developed to get ideas and answer fundamental questions of flow and migration in geologic media. The setup was made of a granite block of 50x50cm scale and a transparent acrylate plate. The tracers used in this experiments were tritiated water, anions, and sorbing cations as well as an organic dye, eosine, to visualize migration paths. The migration plumes were taken with a digital camera as a function of time and stored as digital images. A migration model was also developed to describe and identify the transport processes. Computer simulation was carried out not only for the hydraulic behavior such as distributions of pressure and flow vectors in the fracture but also for the migration plume and the elution curves.

  9. Stable Flows over Time

    Directory of Open Access Journals (Sweden)

    Jannik Matuschke

    2013-08-01

    Full Text Available In this paper, the notion of stability is extended to network flows over time. As a useful device in our proofs, we present an elegant preflow-push variant of the Gale-Shapley algorithm that operates directly on the given network and computes stable flows in pseudo-polynomial time, both in the static flow and the flow over time case. We show periodical properties of stable flows over time on networks with an infinite time horizon. Finally, we discuss the influence of storage at vertices, with different results depending on the priority of the corresponding holdover edges.

  10. Signal flow analysis

    CERN Document Server

    Abrahams, J R; Hiller, N

    1965-01-01

    Signal Flow Analysis provides information pertinent to the fundamental aspects of signal flow analysis. This book discusses the basic theory of signal flow graphs and shows their relation to the usual algebraic equations.Organized into seven chapters, this book begins with an overview of properties of a flow graph. This text then demonstrates how flow graphs can be applied to a wide range of electrical circuits that do not involve amplification. Other chapters deal with the parameters as well as circuit applications of transistors. This book discusses as well the variety of circuits using ther

  11. Separation of flow

    CERN Document Server

    Chang, Paul K

    2014-01-01

    Interdisciplinary and Advanced Topics in Science and Engineering, Volume 3: Separation of Flow presents the problem of the separation of fluid flow. This book provides information covering the fields of basic physical processes, analyses, and experiments concerning flow separation.Organized into 12 chapters, this volume begins with an overview of the flow separation on the body surface as discusses in various classical examples. This text then examines the analytical and experimental results of the laminar boundary layer of steady, two-dimensional flows in the subsonic speed range. Other chapt

  12. Experimental Study of Tip Vortex Flow from a Periodically Pitched Airfoil Section

    Science.gov (United States)

    Zaman, KBMQ; Fagan, A. F.; Mankbadi, M. R.

    2016-01-01

    An experimental investigation of a tip vortex from a NACA0012 airfoil is conducted in a low-speed wind tunnel at a chord Reynolds number of 4x10(exp 4). Initially, data for a stationary airfoil held at various angles-of-attack (alpha) are gathered. Detailed surveys are done for two cases: alpha=10 deg with attached flow and alpha=25 deg with massive flow separation on the upper surface. Distributions of various properties are obtained using hot-wire anemometry. Data include mean velocity, streamwise vorticity and turbulent stresses at various streamwise locations. For all cases, the vortex core is seen to involve a mean velocity deficit. The deficit apparently traces to the airfoil wake, part of which gets wrapped by the tip vortex. At small alpha, the vortex is laminar within the measurement domain. The strength of the vortex increases with increasing alpha but undergoes a sudden drop around alpha (is) greater than 16 deg. The drop in peak vorticity level is accompanied by transition and a sharp rise in turbulence within the core. Data are also acquired with the airfoil pitched sinusoidally. All oscillation cases pertain to a mean alpha=15 deg while the amplitude and frequency are varied. An example of phase-averaged data for an amplitude of +/-10 deg and a reduced frequency of k=0.2 is discussed. All results are compared with available data from the literature shedding further light on the complex dynamics of the tip vortex.

  13. Redistribution of an inlet temperature distortion in an axial flow turbine stage

    Science.gov (United States)

    Butler, T. L.; Sharma, O. P.; Joslyn, H. D.; Dring, R. P.

    1986-06-01

    The results of an experimental program aimed at determining the extent of the redistribution of an inlet temperature distortion in an axial flow turbine stage are presented. The program was conducted in a large-scale, low speed, single stage turbine where air, seeded with CO2 was introduced at one circumferential location upstream of the inlet guide vane. The migration of the seeded air through the turbine was determined by sensing CO2 concentration inside the stage. A temperature distortion was introduced by heating the seeded air. The CO2 concentration contours measured downstream of the vane showed little change with heating, indicating that the vane flowfield was relatively unaffected by the introduction of the temperature distortion. However, the CO2 contours observed on the rotor airfoil surfaces for the case with inlet heating indicated segregation of hot and cold gas, with the higher temperature gas migrating to the pressure side and the lower temperature gas migrating to the suction side. Significant increases in rotor secondary flow were also observed.

  14. Impact of Periodic Unsteadiness on Performance and Heat Load in Axial Flow Turbomachines

    Science.gov (United States)

    Sharma, Om P.; Stetson, Gary M.; Daniels, William A,; Greitzer, Edward M.; Blair, Michael F.; Dring, Robert P.

    1997-01-01

    Results of an analytical and experimental investigation, directed at the understanding of the impact of periodic unsteadiness on the time-averaged flows in axial flow turbomachines, are presented. Analysis of available experimental data, from a large-scale rotating rig (LSRR) (low speed rig), shows that in the time-averaged axisymmetric equations the magnitude of the terms representing the effect of periodic unsteadiness (deterministic stresses) are as large or larger than those due to random unsteadiness (turbulence). Numerical experiments, conducted to highlight physical mechanisms associated with the migration of combustor generated hot-streaks in turbine rotors, indicated that the effect can be simulated by accounting for deterministic stress like terms in the time-averaged mass and energy conservation equations. The experimental portion of this program shows that the aerodynamic loss for the second stator in a 1-1/2 stage turbine are influenced by the axial spacing between the second stator leading edge and the rotor trailing edge. However, the axial spacing has little impact on the heat transfer coefficient. These performance changes are believed to be associated with the change in deterministic stress at the inlet to the second stator. Data were also acquired to quantify the impact of indexing the first stator relative to the second stator. For the range of parameters examined, this effect was found to be of the same order as the effect of axial spacing.

  15. Numerical simulations of sink-flow boundary layers over rough surfaces

    Science.gov (United States)

    Yuan, J.; Piomelli, U.

    2014-01-01

    Turbulent sink flows over smooth or rough walls with sand-grain roughness are studied using large-eddy and direct numerical simulations. Mild and strong levels of acceleration are applied, yielding a wide range of Reynolds number (Reθ = 372 - 2748) and cases close to the reverse-transitional state. Flow acceleration and roughness are shown to exert opposite effects on boundary-layer integral parameters, on the Reynolds stresses, budgets of turbulent kinetic energy, and properties of turbulent structures in the vicinity of the rough surface; statistics exhibit similarity when plotted using inner scaling for cases with the same roughness Reynolds number, k+. Acceleration leads to a decrease of k+, while roughness increases it. For cases with higher k+, the low-speed streaks become destabilized, and turbulent structures near the wall are distributed more uniformly in the wall-parallel plane; they are less extended in the streamwise direction, but more densely packed. Higher k+ also causes decorrelation of the outer-layer hairpin packets with the near-wall structures, probably due to the direct impact of random roughness elements on the hairpin legs. Wall-similarity applies for the fully turbulent cases, in which the outer-layer turbulent statistics are affected by acceleration only. It is shown that being in the hydraulically smooth regime is a necessary condition for reverse-transition, supporting the idea that relaminarization starts from the inner region, where roughness effects dominate.

  16. A Two Element Laminar Flow Airfoil Optimized for Cruise. M.S. Thesis

    Science.gov (United States)

    Steen, Gregory Glen

    1994-01-01

    Numerical and experimental results are presented for a new two-element, fixed-geometry natural laminar flow airfoil optimized for cruise Reynolds numbers on the order of three million. The airfoil design consists of a primary element and an independent secondary element with a primary to secondary chord ratio of three to one. The airfoil was designed to improve the cruise lift-to-drag ratio while maintaining an appropriate landing capability when compared to conventional airfoils. The airfoil was numerically developed utilizing the NASA Langley Multi-Component Airfoil Analysis computer code running on a personal computer. Numerical results show a nearly 11.75 percent decrease in overall wing drag with no increase in stall speed at sailplane cruise conditions when compared to a wing based on an efficient single element airfoil. Section surface pressure, wake survey, transition location, and flow visualization results were obtained in the Texas A&M University Low Speed Wind Tunnel. Comparisons between the numerical and experimental data, the effects of the relative position and angle of the two elements, and Reynolds number variations from 8 x 10(exp 5) to 3 x 10(exp 6) for the optimum geometry case are presented.

  17. Flow field behavior with Reynolds number variance around a spiked body

    Science.gov (United States)

    Khurana, Shashank; Suzuki, Kojiro; Rathakrishnan, Ethirajan

    2016-10-01

    An experimental visualization study was performed to investigate the dependence of the pressure hill height and the influence zone expanse, for flow past a spiked body with different nose configurations, over a Reynolds number range from 2278 to 4405 to establish the vortex shedding process, and applicability in low speed flow regime for effective pressure reduction. It is found that the spike reduces the radius of curvature of the approaching streamline, leading to the deflection of the streamlines towards the shoulder of the basic body, resulting in a narrow zone of the positive pressure hill at the body nose. It is also observed that the pressure hill length and the influence zone expanse decrease with the introduction of spike over the present range of Reynolds numbers. For Reynolds numbers less than 2700, spike with conical nose is found to be more efficient than the spikes with other nose shapes of the present study in reducing the positive pressure at the nose of the blunt body. For higher Reynolds numbers, greater than 2700, the size of the vortex at the junction of the spike and basic body is the largest for the spike with hemispherical nose, and emerges as a potential candidate for application in possible wind-design resistant structures.

  18. Development of Advanced High Lift Leading Edge Technology for Laminar Flow Wings

    Science.gov (United States)

    Bright, Michelle M.; Korntheuer, Andrea; Komadina, Steve; Lin, John C.

    2013-01-01

    This paper describes the Advanced High Lift Leading Edge (AHLLE) task performed by Northrop Grumman Systems Corporation, Aerospace Systems (NGAS) for the NASA Subsonic Fixed Wing project in an effort to develop enabling high-lift technology for laminar flow wings. Based on a known laminar cruise airfoil that incorporated an NGAS-developed integrated slot design, this effort involved using Computational Fluid Dynamics (CFD) analysis and quality function deployment (QFD) analysis on several leading edge concepts, and subsequently down-selected to two blown leading-edge concepts for testing. A 7-foot-span AHLLE airfoil model was designed and fabricated at NGAS and then tested at the NGAS 7 x 10 Low Speed Wind Tunnel in Hawthorne, CA. The model configurations tested included: baseline, deflected trailing edge, blown deflected trailing edge, blown leading edge, morphed leading edge, and blown/morphed leading edge. A successful demonstration of high lift leading edge technology was achieved, and the target goals for improved lift were exceeded by 30% with a maximum section lift coefficient (Cl) of 5.2. Maximum incremental section lift coefficients ( Cl) of 3.5 and 3.1 were achieved for a blown drooped (morphed) leading edge concept and a non-drooped leading edge blowing concept, respectively. The most effective AHLLE design yielded an estimated 94% lift improvement over the conventional high lift Krueger flap configurations while providing laminar flow capability on the cruise configuration.

  19. Flow Field Simulation and Noise Control of a Twin-Screw Engine-Driven Supercharger

    Directory of Open Access Journals (Sweden)

    Tao Wang

    2016-01-01

    Full Text Available With the advantages of good low-speed torque capability and excellent instant response performance, twin-screw superchargers have great potential in the automobile market, but the noise of these superchargers is the main factor that discourages their use. Therefore, it is important to study their noise mechanism and methods of reducing it. This study included a transient numerical simulation of a twin-screw supercharger flow field with computational fluid dynamics software and an analysis of the pressure field of the running rotor. The results showed that overcompression was significant in the compression end stage of the supercharger, resulting in a surge in airflow to a supersonic speed and the production of shock waves that resulted in loud noise. On the basis of these findings, optimization of the supercharger is proposed, including expansion of the supercharger exhaust orifice and creation of a slot along the direction of the rotor spiral normal line at the exhaust port, so as to reduce the compression end pressure, improve the exhaust flow channel, and weaken the source of the noise. Experimental results showed that the noise level value of the improved twin-screw supercharger was significantly lower at the same speed than the original model, with an average decrease of about 5 dB (A.

  20. Beyond the Knudsen number: assessing thermodynamic non-equilibrium in gas flows

    CERN Document Server

    Meng, Jianping; Reese, Jason M; Zhang, Yonghao

    2012-01-01

    For more than 150 years the Navier-Stokes equations for thermodynamically quasi-equilibrium flows have been the cornerstone of modern computational fluid dynamics that underpins new fluid technologies. However, the applicable regime of the Navier-Stokes model in terms of the level of thermodynamic non-equilibrium in the local flowfield is not clear especially for hypersonic and low-speed micro/nano flows. Here, we re-visit the Navier-Stokes model in the framework of Boltzmann statistics, and propose a new and more appropriate way of assessing non-equilibrium in the local flowfield, and the corresponding appropriateness of the Navier-Stokes model. Our theoretical analysis and numerical simulations confirm our proposed method. Through molecular dynamics simulations we reveal that the commonly-used Knudsen number, or a parametric combination of Knudsen and Mach numbers, may not be sufficient to accurately assess the departure of flowfields from equilibrium, and the applicability of the Navier-Stokes model.

  1. Observing hydrological processes: recent advancements in surface flow monitoring through image analysis

    Science.gov (United States)

    Tauro, Flavia; Grimaldi, Salvatore

    2017-04-01

    Recently, several efforts have been devoted to the design and development of innovative, and often unintended, approaches for the acquisition of hydrological data. Among such pioneering techniques, this presentation reports recent advancements towards the establishment of a novel noninvasive and potentially continuous methodology based on the acquisition and analysis of images for spatially distributed observations of the kinematics of surface waters. The approach aims at enabling rapid, affordable, and accurate surface flow monitoring of natural streams. Flow monitoring is an integral part of hydrological sciences and is essential for disaster risk reduction and the comprehension of natural phenomena. However, water processes are inherently complex to observe: they are characterized by multiscale and highly heterogeneous phenomena which have traditionally demanded sophisticated and costly measurement techniques. Challenges in the implementation of such techniques have also resulted in lack of hydrological data during extreme events, in difficult-to-access environments, and at high temporal resolution. By combining low-cost yet high-resolution images and several velocimetry algorithms, noninvasive flow monitoring has been successfully conducted at highly heterogeneous scales, spanning from rills to highly turbulent streams, and medium-scale rivers, with minimal supervision by external users. Noninvasive image data acquisition has also afforded observations in high flow conditions. Latest novelties towards continuous flow monitoring at the catchment scale have entailed the development of a remote gauge-cam station on the Tiber River and integration of flow monitoring through image analysis with unmanned aerial systems (UASs) technology. The gauge-cam station and the UAS platform both afford noninvasive image acquisition and calibration through an innovative laser-based setup. Compared to traditional point-based instrumentation, images allow for generating surface

  2. Interaction of the main and shroud leakage flow and their impact on the losses of an axial turbine. Shroud leakage flow effects III - final report; Interaktion von Haupt- und Deckbandstroemung und ihre Auswirkung auf Verluste in einer axialen Turbomaschine. Deckbandstroemungseinfluss III - Abschlussbericht

    Energy Technology Data Exchange (ETDEWEB)

    Anker, J.E. [Stuttgart Univ. (DE). Inst. fuer Thermische Stroemungsmaschinen und Maschinenlaboratorium (ITSM); Wolter, K. [Ruhr-Univ. Bochum (DE). Lehrstuhl fuer Dampf- und Gasturbinen (DGT); Jung, A.R. [Siemens AG, Muelheim/Ruhr (Germany)

    2004-07-01

    This report presents the results of the FVV research project Deckbandstroemungseinfluss III (Shroud leakage flow effects III) where the flow field in a 1.5-stage low-speed axial turbine with a shrouded rotor was studied experimentally and numerically. Whereas in two earlier projects in this series (Deckbandstroemungseinfluss I and II) it were focused upon the impact of the leakage flow on the main flow, the experimental and numerical investigations of this project concentrate on the effects occurring within the labyrinth seal and on a method to simplify the modeling of labyrinth seals within multi-stage calculations. The measurements were carried out at three operating points and at five planes in the labyrinth seal using miniature pneumatic probes and miniature hot wires. The experimental data quantify the leakage flow and the vortex structures in the labyrinth seal of the shrouded rotor and complete the results of the previous projects. Due to their high spatial and temporal resolution, they provide a reference for fully 3D unsteady simulations of leakage flow in axial turbomachinery. In this report en empirical labyrinth seal leakage model is presented that allows simplified multistage calculations of shrouded turbomachinery. Its constants were determined using the results from a numerical study in which the geometric parameters of the labyrinth seal were varied. The model could be calibrated to give close agreement with the results of the reference simulations. Thus, good results are also expected when substituting the full discretisation of the labyrinth seal with the newly developed model. (orig.)

  3. Group flow, complex flow, unit vector flow, and the (2+ϵ)-flow conjecture

    DEFF Research Database (Denmark)

    Thomassen, Carsten

    2014-01-01

    If F is a (possibly infinite) subset of an abelian group Γ, then we define f(F,Γ) as the smallest natural number such that every f(F,Γ)-edge-connected (finite) graph G has a flow where all flow values are elements in F. We prove that f(F,Γ) exists if and only if some odd sum of elements in F equals...... some even sum. We discuss various instances of this problem. We prove that every 6-edge-connected graph has a flow whose flow values are the three roots of unity in the complex plane. If the edge-connectivity 6 can be reduced, then it can be reduced to 4, and the 3-flow conjecture follows. We prove...... that every 14-edge-connected graph has a flow whose flow values are the five roots of unity in the complex plane. Any such flow is balanced modulo 5. So, if the edge-connectivity 14 can be reduced to 9, then the 5-flow conjecture follows, as observed by F. Jaeger. We use vector flow to prove that, for each...

  4. Study of Sweep and Induced Dihedral Effects in Subsonic Axial Flow Compressor Passages—Part II: Detailed Study of the Effects on Tip Leakage Phenomena

    Directory of Open Access Journals (Sweden)

    P. V. Ramakrishna

    2010-01-01

    Full Text Available This article presents the detailed study of rotor tip leakage related phenomena in a low speed axial compressor rotor passages for three sweep configurations [Unswept (UNS, Tip Chordline Swept (TCS and Axially Swept (AXS]. Fifteen domains are numerically studied with 5 sweep configurations (0°, 20° TCS, 30° TCS, 20° AXS, and 30° AXS and for 3 tip clearances (0.0%, 0.7% and 2.7% of the blade chord. Results were well validated with experimental data. Observations near the tip reveal that UNS rotor shows high sensitivity than the swept rotors in the blade pressure distribution with change in tip clearance. AXS rotor has high loading capability and less tip clearance effect on blade loading at the near stall mass flow. Downstream shift of the vortex rollup along the chord is observed with increased flow coefficient and increment in the tip gap height. In particular, the effect of flow coefficient is more predominant on this effect. Tip vortex-related flow blockage is less with the swept rotors. Among the rotors, the AXS rotor is found to incur low total pressure losses attributable to tip leakage. Effect of incidence is observed on the flow leakage direction.

  5. Concentric Split Flow Filter

    Science.gov (United States)

    Stapleton, Thomas J. (Inventor)

    2015-01-01

    A concentric split flow filter may be configured to remove odor and/or bacteria from pumped air used to collect urine and fecal waste products. For instance, filter may be designed to effectively fill the volume that was previously considered wasted surrounding the transport tube of a waste management system. The concentric split flow filter may be configured to split the air flow, with substantially half of the air flow to be treated traveling through a first bed of filter media and substantially the other half of the air flow to be treated traveling through the second bed of filter media. This split flow design reduces the air velocity by 50%. In this way, the pressure drop of filter may be reduced by as much as a factor of 4 as compare to the conventional design.

  6. TRANSIMS traffic flow characteristics

    CERN Document Server

    Nagel, K; Pieck, M; Donnelly, R; Barrett, C L; Nagel, Kai; Stretz, Paula; Pieck, Martin; Donnelly, Rick; Barrett, Christopher L.

    1997-01-01

    Knowledge of fundamental traffic flow characteristics of traffic simulation models is an essential requirement when using these models for the planning, design, and operation of transportation systems. In this paper we discuss the following: a description of how features relevant to traffic flow are currently under implementation in the TRANSIMS microsimulation, a proposition for standardized traffic flow tests for traffic simulation models, and the results of these tests for two different versions of the TRANSIMS microsimulation.

  7. Polyoxometalate flow battery

    Science.gov (United States)

    Anderson, Travis M.; Pratt, Harry D.

    2016-03-15

    Flow batteries including an electrolyte of a polyoxometalate material are disclosed herein. In a general embodiment, the flow battery includes an electrochemical cell including an anode portion, a cathode portion and a separator disposed between the anode portion and the cathode portion. Each of the anode portion and the cathode portion comprises a polyoxometalate material. The flow battery further includes an anode electrode disposed in the anode portion and a cathode electrode disposed in the cathode portion.

  8. A neural flow estimator

    DEFF Research Database (Denmark)

    Jørgensen, Ivan Harald Holger; Bogason, Gudmundur; Bruun, Erik

    1995-01-01

    This paper proposes a new way to estimate the flow in a micromechanical flow channel. A neural network is used to estimate the delay of random temperature fluctuations induced in a fluid. The design and implementation of a hardware efficient neural flow estimator is described. The system...... is implemented using switched-current technique and is capable of estimating flow in the μl/s range. The neural estimator is built around a multiplierless neural network, containing 96 synaptic weights which are updated using the LMS1-algorithm. An experimental chip has been designed that operates at 5 V...

  9. Supersonic flows over cavities

    Institute of Scientific and Technical Information of China (English)

    Tianwen FANG; Meng DING; Jin ZHOU

    2008-01-01

    The characteristics of supersonic cold flows over cavities were investigated experimentally and numer-ically, and the effects of cavities of different sizes on super-sonic flow field were analyzed. The results indicate that the ratio of length to depth L/D within the range of 5-9 has little relevance to integral structures of cavity flow. The bevel angle of the rear wall does not alter the overall structure of the cavity flow within the range of 30°-60°, but it can exert obvious effect on the evolvement of shear layer and vortexes in cavities.

  10. Retinal flow cytometer.

    Science.gov (United States)

    Alt, C; Veilleux, I; Lee, H; Pitsillides, C M; Côté, D; Lin, C P

    2007-12-01

    The in vivo flow cytometer is an instrument capable of continuous, real-time monitoring of fluorescently labeled cells in the circulation without the need to draw blood samples. However, the original system probes a single vessel in the mouse ear; the small sample volume limits the sensitivity of the technique. We describe an in vivo retinal flow cytometer that simultaneously probes five artery-vein pairs in the mouse eye by circularly scanning a small laser spot rapidly around the optic nerve head. We demonstrate that the retinal flow cytometer detects about five times more cells per minute than the original in vivo flow cytometer does in the ear.

  11. Excess flow shutoff valve

    Energy Technology Data Exchange (ETDEWEB)

    Kiffer, Micah S.; Tentarelli, Stephen Clyde

    2016-02-09

    Excess flow shutoff valve comprising a valve body, a valve plug, a partition, and an activation component where the valve plug, the partition, and activation component are disposed within the valve body. A suitable flow restriction is provided to create a pressure difference between the upstream end of the valve plug and the downstream end of the valve plug when fluid flows through the valve body. The pressure difference exceeds a target pressure difference needed to activate the activation component when fluid flow through the valve body is higher than a desired rate, and thereby closes the valve.

  12. Asymmetric flow networks

    OpenAIRE

    Olaizola Ortega, María Norma; Valenciano Llovera, Federico

    2012-01-01

    This paper provides a new model of network formation that bridges the gap between the two benchmark models by Bala and Goyal, the one-way flow model, and the two-way flow model, and includes both as particular extreme cases. As in both benchmark models, in what we call an "asymmetric flow" network a link can be initiated unilaterally by any player with any other, and the flow through a link towards the player who supports it is perfect. Unlike those models, in the opposite direction there is ...

  13. The other spectral flow

    CERN Document Server

    Gato-Rivera, Beatriz; Gato-Rivera, Beatriz; Rosado, Jose Ignacio

    1995-01-01

    Recently we showed that the spectral flow acting on the N=2 twisted topological theories gives rise to a topological algebra automorphism. Here we point out that the untwisting of that automorphism leads to a spectral flow on the untwisted N=2 superconformal algebra which is different from the usual one. This "other" spectral flow does not interpolate between the chiral ring and the antichiral ring. In particular, it maps the chiral ring into the chiral ring and the antichiral ring into the antichiral ring. We discuss the similarities and differences between both spectral flows. We also analyze their action on null states.

  14. Experimental Investigation of 3-D flow fields around the mouth of the Dwarf Seahorse during attacks on planktonic prey

    Science.gov (United States)

    Gemmell, Brad; Buskey, Edward; Sheng, Jian

    2009-11-01

    Copepods are an important planktonic food source for fish species. High predation has led to the development of effective escape responses with short reaction times (less than 2 ms), maximum escape velocities of over 500 body lengths per second and shear sensitivity as low as 1.5s-1. Using high speed digital holography (2 kfps), we measure 3-D distributions of velocity generated by a dwarf seahorse (Hippocampus zosterae) during attacks on its copepod prey, Acartia tonsa. It is found that successful attacks often produce smaller or even no detectable hydrodynamic disturbances around the strike zone, when compared to unsuccessful attempts. In this paper, we will provide quantitative characterization of this ``low-flow'' zone. Further, to elucidate the role of a possible geometrical advantage of the seahorse's head in minimizing its bow wave, high-speed time resolved PIV measurements are conducted in a low-speed water tunnel. On-going analysis will provide insights and implications in understanding the dynamics of flows around the stagnation point at high Reynolds number flow. Sponsored by NSF.

  15. Control of Flow Structure on Non-Slender Delta Wing: Bio-inspired Edge Modifications, Passive Bleeding, and Pulsed Blowing

    Science.gov (United States)

    Yavuz, Mehmet Metin; Celik, Alper; Cetin, Cenk

    2016-11-01

    In the present study, different flow control approaches including bio-inspired edge modifications, passive bleeding, and pulsed blowing are introduced and applied for the flow over non-slender delta wing. Experiments are conducted in a low speed wind tunnel for a 45 degree swept delta wing using qualitative and quantitative measurement techniques including laser illuminated smoke visualization, particle image velocimety (PIV), and surface pressure measurements. For the bio-inspired edge modifications, the edges of the wing are modified to dolphin fluke geometry. In addition, the concept of flexion ratio, a ratio depending on the flexible length of animal propulsors such as wings, is introduced. For passive bleeding, directing the free stream air from the pressure side of the planform to the suction side of the wing is applied. For pulsed blowing, periodic air injection through the leading edge of the wing is performed in a square waveform with 25% duty cycle at different excitation frequencies and compared with the steady and no blowing cases. The results indicate that each control approach is quite effective in terms of altering the overall flow structure on the planform. However, the success level, considering the elimination of stall or delaying the vortex breakdown, depends on the parameters in each method.

  16. Stereoscopic particle image velocimetry measurements of the three-dimensional flow field of a descending autorotating mahogany seed (Swietenia macrophylla).

    Science.gov (United States)

    Salcedo, E; Treviño, C; Vargas, R O; Martínez-Suástegui, L

    2013-06-01

    An experimental investigation of near field aerodynamics of wind dispersed rotary seeds has been performed using stereoscopic digital particle image velocimetry (DPIV). The detailed three-dimensional flow structure of the leading-edge vortex (LEV) of autorotating mahogany seeds (Swietenia macrophylla) in a low-speed vertical wind tunnel is revealed for the first time. The results confirm that the presence of strong spanwise flow and strain produced by centrifugal forces through a spiral vortex are responsible for the attachment and stability of the LEV, with its core forming a cone pattern with a gradual increase in vortex size. The LEV appears at 25% of the wingspan, increases in size and strength outboard along the wing, and reaches its maximum stability and spanwise velocity at 75% of the wingspan. At a region between 90 and 100% of the wingspan, the strength and stability of the vortex core decreases and the LEV re-orientation/inflection with the tip vortex takes place. In this study, the instantaneous flow structure and the instantaneous velocity and vorticity fields measured in planes parallel to the free stream direction are presented as contour plots using an inertial and a non-inertial frame of reference. Results for the mean aerodynamic thrust coefficients as a function of the Reynolds number are presented to supplement the DPIV data.

  17. PIV study on a shock-induced separation in a transonic flow

    Energy Technology Data Exchange (ETDEWEB)

    Sartor, Fulvio; Losfeld, Gilles; Bur, Reynald [ONERA, Meudon (France)

    2012-09-15

    A transonic interaction between a steady shock wave and a turbulent boundary layer in a Mach 1.4 channel flow is experimentally investigated by means of particle image velocimetry (PIV). In the test section, the lower wall is equipped with a contour profile shaped as a bump allowing flow separation. The transonic interaction, characterized by the existence in the outer flow of a lambda shock pattern, causes the separation of the boundary layer, and a low-speed recirculating bubble is observed downstream of the shock foot. Two-component PIV velocity measurements have been performed using an iterative gradient-based cross-correlation algorithm, providing high-speed and flexible calculations, instead of the classic multi-pass processing with FFT-based cross-correlation. The experiments are performed discussing all the hypotheses linked to the experimental set-up and the technique of investigation such as the two-dimensionality assumption of the flow, the particle response assessment, the seeding system, and the PIV correlation uncertainty. Mean velocity fields are presented for the whole interaction with particular attention for the recirculating bubble downstream of the detachment, especially in the mixing layer zone where the effects of the shear stress are most relevant. Turbulence is discussed in details, the results are compared to previous study, and new results are given for the turbulent production term and the return to isotropy mechanism. Finally, using different camera lens, a zoom in the vicinity of the wall presents mean and turbulent velocity fields for the incoming boundary layer. (orig.)

  18. Tetrahedral-Mesh Simulation of Turbulent Flows with the Space-Time Conservative Schemes

    Science.gov (United States)

    Chang, Chau-Lyan; Venkatachari, Balaji; Cheng, Gary C.

    2015-01-01

    isotropic turbulent flow decay, at a relatively high turbulent Mach number, show a nicely behaved spectral decay rate for medium to high wave numbers. The high-order CESE schemes offer very robust solutions even with the presence of strong shocks or widespread shocklets. The explicit formulation in conjunction with a close to unity theoretical upper Courant number bound has the potential to offer an efficient numerical framework for general compressible turbulent flow simulations with unstructured meshes.

  19. Flow chemistry is starting to flow

    NARCIS (Netherlands)

    Duisterwinkel, A.E.

    2012-01-01

    One good thing about this symposium on flow chemistry is that at least half of the papers was on actual applications: summarized one member of the audience of the IPIT symposium in Rotterdam, 25 May 2012. This remark can be viewed as a compliment to the organizer, TNO, a Dutch contract research orga

  20. Simulation of inertial fibre orientation in turbulent flow

    Science.gov (United States)

    Njobuenwu, Derrick O.; Fairweather, Michael

    2016-06-01

    The spatial and orientational behaviour of fibres within a suspension influences the rheological and mechanical properties of that suspension. An Eulerian-Lagrangian framework to simulate the behaviour of fibres in turbulent flows is presented. The framework is intended for use in simulations of non-spherical particles with high Reynolds numbers, beyond the Stokesian regime, and is a computationally efficient alternative to existing Stokesian models for fibre suspensions in turbulent flow. It is based on modifying available empirical drag correlations for the translation of non-spherical particles to be orientation dependent, accounting for the departure in shape from a sphere. The orientational dynamics of a particle is based on the framework of quaternions, while its rotational dynamics is obtained from the solution of the Euler equation of rotation subject to external torques on the particle. The fluid velocity and turbulence quantities are obtained using a very high-resolution large eddy simulation with dynamic calibration of the sub-grid scale energy containing fluid motions. The simulation matrix consists of four different fibre Stokes numbers (St = 1, 5, 25, and 125) and five different fibre aspect ratios (λ = 1.001, 3, 10, 30, and 50), with results considered at four distances from a channel wall (in the viscous sub-layer, buffer, and fully turbulent regions), which are taken as a measure of the flow velocity gradient, all at a constant fibre to fluid density ratio (ρp/ρ = 760) and shear Reynolds number Reτ = 150. The simulated fibre orientation, concentration, and streakiness confirm previous experimentally observed characteristics of fibre behaviour in turbulence, and that of direct numerical simulations of fibres in Stokesian, or creeping flow, regimes. The fibres exhibit translational motion similar to spheres, where they tend to accumulate in the near-wall (viscous sub-layer and buffer) region and preferentially concentrate in regions of low-speed