An improved version of the CSCM implicit Navier-Stokes solver with a flexible data structure has been applied, in conjunction with a sophisticated patched grid system, to the aerodynamic analysis of hypersonic axisymmetric contoured nozzles of the NASA-Ames 3.5-foot hypersonic wind tunnel. The results obtained are found to be in good agreement with experiment. Based on the analysis, a newly designed throat contour for the Mach 14 nozzle has been recommended.


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    Titel :

    Aerodynamic design modification of a hypersonic wind tunnel nozzle by CSCM with high order accuracy


    Beteiligte:
    Yang, J. Y. (Autor:in) / Lombard, C. K. (Autor:in) / Luh, R. C.-C. (Autor:in) / Nagaraj, N. (Autor:in) / Codding, W. H. (Autor:in)

    Erscheinungsdatum :

    1987-06-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :