The NASA-Ames/Boeing unsteady thin-layer Navier-Stokes code was used to calculate a generic wing/fuselage configuration at a Mach number of 25. Calculations were obtained with perfect gas and with chemical equilibrium air assumption; the surface temperature were prescribed, the results of the two solutions are compared in terms of distribution of pressure, density, temperature, Mach number, ratio of specific heat and heat transfer.


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    Title :

    Navier-Stokes simulation of a hypersonic generic wing/fuselage


    Additional title:

    Allgemeine Navier-Stokes Simulation fuer hypersonisch umstroemte Tragfluegel-Rumpf Verbindungen


    Contributors:
    Wai, J.C. (author) / Dao, S.C. (author) / Chaussee, D. (author)

    Published in:

    AIAA-Papers ; Jun ; 1-12


    Publication date :

    1987


    Size :

    12 Seiten, 12 Bilder, 6 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English