A Numerical Study of Supersonic Flow Over a Compression Corner with Different Incoming Boundary Layer Profiles PDF Download
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Author: S. C. Holmes
Publisher:
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Languages : en
Pages :
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Author: S. C. Holmes
Publisher:
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Category :
Languages : en
Pages :
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Author: Kamlesh Kapoor
Publisher:
ISBN:
Category :
Languages : en
Pages : 18
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Author:
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ISBN:
Category : Fluid dynamics
Languages : en
Pages : 390
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Author: G. D. Senechal
Publisher:
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Category : Aerodynamics, Supersonic
Languages : en
Pages : 61
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Book Description
A numerical study has been made of the nature of the solution to the supersonic boundary-layer equations when the flow separates from the surface. To this end, implicit finite difference solutions t the governing equations are obtained for linearly and quadratically retarded flows over flat plates for a Mach number range of 2 to 15. Both extremely hot and cold wall conditions are considered. Also, solutions for flow on a compression ramp are obtained with and without including the boundary layer's free interaction with the local freestream. The results of this study indicate that non-interacting flows are singular at separation and that free interaction effects reduces singularity. An alternate means of numerically smearing out the singularity and proceeding past separation is also presented.
Author: Bernardo Fortunato
Publisher:
ISBN:
Category :
Languages : en
Pages : 160
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Author:
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Category : Aeronautics
Languages : en
Pages : 590
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Author: John C. Adams
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 98
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Book Description
An analytical approach toward numerical calculation of the three-dimensional turbulent boundary layer on a sharp cone at incidence under supersonic and hypersonic flow conditions is presented. The theoretical model is based on implicit finite-difference integration of the governing three-dimensional turbulent boundary-layer equations in conjunction with a three-dimensional scalar eddy-viscosity model of turbulence. Comparison is made of present theory with detailed experimental measurements of the three-dimensional turbulent boundary-layer structure (velocity and temperature profiles), the surface streamline direction (obtained via an oil-flow technique) and surface heat-transfer rate.
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781792705748
Category :
Languages : en
Pages : 30
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A two-dimensional computational code, PRLUS2D, which was developed for the reactive propulsive flows of ramjets and scramjets, was validated for two-dimensional shock-wave/turbulent-boundary-layer interactions. The problem of compression corners at supersonic speeds was solved using the RPLUS2D code. To validate the RPLUS2D code for hypersonic speeds, it was applied to a realistic hypersonic inlet geometry. Both the Baldwin-Lomax and the Chien two-equation turbulence models were used. Computational results showed that the RPLUS2D code compared very well with experimentally obtained data for supersonic compression corner flows, except in the case of large separated flows resulting from the interactions between the shock wave and turbulent boundary layer. The computational results compared well with the experiment results in a hypersonic NASA P8 inlet case, with the Chien two-equation turbulence model performing better than the Baldwin-Lomax model. Kapoor, Kamlesh and Anderson, Bernhard H. and Shaw, Robert J. Glenn Research Center NASA-TM-106580, E-8840, NAS 1.15:106580 RTOP 537-02-23...
Author: Maurice Tucker
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 30
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An analytical method is presented for obtaining turbulent temperature recovery factors for a thermally insulated surface in supersonic flow. The method is an extension of Squire's analysis for incompressible flow. The boundary layer velocity profile is represented by a power law and a similarity is postulated for squared-velocity the static-temperature-difference profiles.
Author: Bernardo Fortunato
Publisher:
ISBN:
Category :
Languages : en
Pages : 92
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Book Description
The compressible and incompressible boundary layer equations are solved for laminar flow past a configuration with an interior (concave) compression region. The approach first employs conformal coordinates to map the body geometry to a flat wall, and then the boundary layer scale laws to identify the principal terms of the compressible counterpart of the Navier-Stokes equations. A Levy-Lees type transformation is identified in these coordinates to simplify the governing equations. These are then solved with a second-order accurate numerical scheme in both the longitudinal and normal directions. Solutions are obtained for adiabatic and 'warm' wall conditions for configurations with and without separation. Emphasis is placed here on achieving accurate reliable results while maintaining minimal computer time expenditure. (Author).
