An aerodynamic prediction technique based on the steady form of the full-potential equation has been applied to a variety of three-dimensional supersonic flow problems exhibiting embedded subsonic regions. A conservative switching scheme is employed to transition from the supersonic relaxation algorithm, and vice versa. Numerical solutions are obtained for a number of complex configurations, including advanced tactical fighter, Langley canard-wing fighter configuration, isolated shuttle orbiter, and mated shuttle orbiter configuration with external tank. The computed results are in good agreement with available experimental data.


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    Title :

    Computation of supersonic flows over three-dimensional configurations


    Contributors:
    Szema, K.-Y. (author) / Riba, W. L. (author) / Shankar, V. (author) / Gorski, J. J. (author)

    Published in:

    Publication date :

    1985-12-01



    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Computation of supersonic flows over three-dimensional configurations

    SZEMA, K.-Y. / RIBA, W. / SHANKAR, V. et al. | AIAA | 1985


    Computation of supersonic flows over three-dimensional configurations

    SZEMA, K.-Y. / RIBA, W. L. / SHANKAR, V. et al. | AIAA | 1985