Three-dimensional transonic viscous flow computations are presented for a generic high-speed accelerator model that includes wing, body, fillets, and a no-flow-through engine nacelle. Solutions are obtained from an algorithm for the compressible Navier-Stokes equations that incorporates an upwind-biased, flux-vector-splitting approach along with longitudinally patched grids. Results are presented for fully turbulent flow assumptions and include correlations with wind-tunnel data. A good quantitative agreement for the forebody surface pressure distribution is achieved between computations and the available wind-tunnel measurements at M∞ = 0.9. Furthermore, it is demonstrated that the flow is stagnating around the boattail region due to separation from the aft-engine cowl lip.


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    Title :

    Transonic Navier-Stokes Solutions About a Generic Hypersonic Configuration


    Contributors:

    Conference:

    28th Aerospace Sciences Meeting ; 1990 ; Reno, NV, US


    Published in:

    Publication date :

    1991-06-01




    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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