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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    Titel :

    Computation of supersonic flows over three-dimensional configurations


    Beteiligte:
    Szema, K.-Y. (Autor:in) / Riba, W. L. (Autor:in) / Shankar, V. (Autor:in) / Gorski, J. J. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    01.12.1985



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    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