The method of Suresh and Liou (1992) is extended, and the resulting explicit noniterative upwind finite-volume algorithm is applied to the integration of 3D parabolized Navier-Stokes equations to model 3D hypersonic real-gas flowfields. The solver is second-order accurate in the marching direction and employs flux-limiters to make the algorithm second-order accurate, with total variation diminishing in the cross-flow direction. The algorithm is used to compute hypersonic flow over a yawed cone and over the Ames All-Body Hypersonic Vehicle. The solutions obtained agree well with other computational results and with experimental data.


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    Titel :

    A comparison of upwind schemes for computation of three-dimensional hypersonic real-gas flows


    Beteiligte:
    Gerbsch, R. A. (Autor:in) / Agarwal, R. K. (Autor:in)

    Kongress:

    AIAA, Atmospheric Flight Mechanics Conference ; 1992 ; Hilton Head Island, SC, United States


    Erscheinungsdatum :

    1992-08-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



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