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Wednesday, July 22, 2020 | History

2 edition of Two- and three-dimensional viscous computations of a hypersonic inlet flow found in the catalog.

Two- and three-dimensional viscous computations of a hypersonic inlet flow

Two- and three-dimensional viscous computations of a hypersonic inlet flow

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Published by National Aeronautics and Space Administration, For sale by the National Technical Information Service in [Washington, DC], [Springfield, Va .
Written in English

    Subjects:
  • Aerodynamics, Hypersonic.,
  • Fluid mechanics.,
  • Mach number.

  • Edition Notes

    Other titlesTwo and three dimensional viscous computations of a hypersonic inlet flow.
    StatementWilliam G. Kunik ... [et al.].
    SeriesNASA technical memorandum -- 88923.
    ContributionsKunik, William G., United States. National Aeronautics and Space Administration.
    The Physical Object
    FormatMicroform
    Pagination1 v.
    ID Numbers
    Open LibraryOL18031800M

    the di culties of designing hypersonic airbreathing engines.1{3 The highly complex ow experienced by three-dimensional hypersonic inlets, demanding performance requirements, and engine design strongly cou-pled to the vehicle create a need for simulation-based design. Therefore, e cient high- delity computation of gradients is desired. The monograph summarizes the results of research of many years in the field of numerical simulation based on the continuum dynamics equations for transonic and supersonic flows of viscous perfect gas in the context of the problems of external aerodynamics, which have been obtained by the authors and their colleagues and published in different domestic journals.

    An analysis of the full, compressible, non-adiabatic boundary-layer equations is presented to describe the so-called ‘throat’ formed when a two-dimensional viscous layer, interacting with a supersonic inviscid outer stream, is accelerated or decelerated through sonic velocity defined in some mean sense. Numerical Simulations of Busemann Hypersonic Inlets as an inlet and simple computations for the efficiency give unphysical results. Graphical Close-up of leading edge region used to form cross-section of three-dimensional wetted inlet. Parameter Value Leading edge radius in. .

      At the 19th Annual Conference on Parallel Computational Fluid Dynamics held in Antalya, Turkey, in May , the most recent developments and implementations of large-scale and grid computing were presented. This book, comprised of the invited and selected papers of this conference, details those advances, which are of particular interest to CFD and CFD-related communities. "A calculation procedure for heat, mass and momentum transfer in three-dimensional parabolic flows," Int. J. Heat Transfer Vol. 15, Schmode, D.; Bertram, V.; E1 Moctar, O.M. "Aerodynamic flow computations for a Superfast ferry", 3r~ High-Performance Marine Vehicles Conf. HIPER'02, Bergen, Speziale, C.G.; Thangham, S., "Analysis of an.


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Two- and three-dimensional viscous computations of a hypersonic inlet flow Download PDF EPUB FB2

TWO- AN0 THREE-DIMENSIONAL VISCOUS COMPUTATIONS OF A HYPERSONIC INLET FLOW William G. Kunik and Thomas J. Benson National Aeronautics and Space Administration Lewis Research Center Cleveland, Ohio and Wing-Fa1 Ng and Arthur. The three-dimensional parabolized Navier-Stokes code has been used to investigate the flow through a Mach inlet.

A two-dimensional parametric study of grid resolution, turbulence modeling and effect of gamma has been done and compared with experimental results. The results show that mesh resolution of the shock waves, real gas effects and turbulence length scaling are very important to get. Two- and three-dimensional viscous computations of a hypersonic inlet flow The three-dimensional parabolized Navier-Stokes code has been used to investigate the flow through a Mach inlet.

A two-dimensional parametric study of grid resolution, turbulence modeling and effect of gamma has been done and compared with experimental results. Computation of Hypersonic Turbulent Flow Over a Rearward Facing Step. Experiments on Shock-Wave/Boundary-Layer Interactions Produced by Two-Dimensional Ramps and Three-Dimensional Obstacles.

Pages Hypersonic Viscous Flow Over Two-Dimensional Ramps. Pages   Supersonic inviscid flow— a three-dimensional characteristics approach Journal of Computational Physics, Vol. 68, No. 2 Effects of nozzle inlet and throat geometry on the specific impulse of solid rocket motorsCited by: In addition, two- and three-dimensional flow calculations were performed for a hypersonic nozzle.

Comparison of the wall pressure results with the published solutions is made for the two. Flow calculations of the hypersonic flow over a two-stage transport vehicle show that the methods allow an economic computation of flows over complex geometries with sharp shocks and no spurious oszillations without using any explicit artificial damping.

Menne S., Weiland C. () Split-Matrix Marching Methods for Three-Dimensional Viscous. Inlets. Various prototypes of hypersonic inlet have been proposed since the s.

Kothari introduced the radial deviation parameter and categorized the inlets as inward-turning inlets, outward-turning inlets, and two-dimensional inlets.

Unlike the other two groups, inward-turning inlets exhibit accumulation of flows in the central part. The research uses CFD to investigate the internal flow of two hypersonic engine inlets: the Hypersonic Research Engine (HRE), a dual-mode ramjet/scramjet, and the Sustained Hypersonic Flight Experiment (SHyFE), a ramjet developed by QinetiQ.

both inviscid and viscous turbulent computations are considered. For the HRE, axisymmetric. InAziz et al. used a time-dependent 3D Reynolds-averaged Navier-Stokes (RANS) code to analyze the flow in a supersonic inlet. InChang et al. used an unsteady 2D code with the SST k-ω turbulence model to simulate a hypersonic inlet.

A generic inlet configuration is considered in order to demonstrate the highly three dimensional viscous flow behavior occurring within rectangular inlets.

Reacting flow computations for simple jet injection as well as for more complex combustion chambers are then discussed in order to show the capability of viscous finite rate chemical. Get this from a library. Two- and three-dimensional viscous computations of a hypersonic inlet flow.

[William G Kunik; United States. National Aeronautics and Space Administration.;]. A Navier-Stokes computer code was validated using a number of two- and three-dimensional configurations for both laminar and turbulent flows. The validation. Performing detailed computations of two dimensional and three dimensional inviscid and viscous flows.

The computations are used to assess the accuracy of the codes, they are intended as standards for comparison purposes (this is the specific purpose of the AGARD WG 07 airfoil computations) and are used to further the understand of fluid physics.

Numerical approaches to simulate viscous hypersonic flows in the continuum- as well as in the gaskinetic-flow regimes are discussed with emphasis on three-dimensional flows.

The ideal-gas continuum flow is simulated with an explicit/implicit finite-difference method for the thin-layer approximation of the time-dependent Navier-Stokes equations. A Three-Dimensional Hypersonic Viscous Interaction F. Hurley. but solutions are readily extracted by means of iterative machine computations.

Answers for the assumed set of flight conditions indicate that the inboard drift of boundary-layer fluid from both sides gives rise to a center-plane region which is three-dimensional in character.

a supersonic flow through an internal/external nozzle-afterbody configuration and its viscous mixing with a hypersonic freestream flow of air is computed using two and three-dimensional upwind, finite volume, Navier-Stokes schemes.

The Reynolds stresses are represented by a. Computing Systems in Engineering Vol. 1, Nospp. 54% /th) $3.{10+0.(X1 Printed in Great Britain. O {} Pergamon Press plc A REVIEW OF REDUCED NAVIER-STOKES COMPUTATIONS FOR COMPRESSIBLE VISCOUS FLOWS S. RUBIN and P. KHOSLA Department of Aerospace Engineering and Engineering Mechanics, University of Cincinnati.

Turbulence Modeling in a Hypersonic Inlet. AIAA Paper Taylor, A., and Ng, W. Analytical Prediction of the Unsteady Lift on a Rotor Caused by Downstream Struts. ASME Paper 87 GT Kunik, W., Benson, T., Ng, W., and Taylor, A.

Two- and Three-Dimensional Viscous Computations of a Hypersonic Inlet. AIAA Paper Numerical Computation of Two-Dimensional Viscous Blunt Body Flows with an Impinging Shock. Hypersonic Laminar Viscous Flow Past Spinning Cones at Angle of Attack.

Ramesh AgarwaI and Three dimensional flow computations with shock fitting. The accuracy improvements in three dimensions are not as great as those in two dimensions. Computation of viscous flowfields in the corner of two intersecting wedges and a turbulent hypersonic inlet configuration show that the inviscid portions of the flowfield are qualitatively improved with the rotated algorithm to both first- and second.An illustration of an open book.

Books. An illustration of two cells of a film strip. Video. An illustration of an audio speaker. Audio. An illustration of a " floppy disk.

Software. An illustration of two photographs. Development of a three-dimensional supersonic inlet flow analysis".A three-dimensional Navier-Stokes solver which utilizes a pressure based method is used to compute the incompressible flow field through the inlet guide vane (IGV) of a high Reynolds number pump.

The solver has precise control of numerical dissipation through the second and fourth order artificial dissipation terms added to the momentum equations.