Experimental data for two three-dimensional intersecting shock-wave/turbulent boundary-layer interaction flows at Mach 8.3 are presented. The test bodies, composed of two sharp fins fastened to a flat plate test bed, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface pressure and heat transfer distributions as well as mean flow field surveys both in the undisturbed and interaction regimes. The data are presented in a convenient form to be used to validate existing or future computational models of these hypersonic flows.


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    Title :

    Hypersonic crossing shock-wave/turbulent-boundary-layer interactions


    Contributors:

    Conference:

    AIAA, Aerospace Sciences Meeting and Exhibit ; 1993 ; Reno, NV, United States


    Publication date :

    1993-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Hypersonic crossing shock-wave/turbulent-boundary-layer interactions

    Kussoy, M. I. / Horstoman, K. C. / Horstman, C. C. | AIAA | 1993


    Hypersonic crossing shock-wave/turbulent-boundary-layer interactions

    KUSSOY, M. / HORSTMAN, K. / HORSTMAN, C. | AIAA | 1993


    Hypersonic crossing shock-wave/turbulent-boundary-layer interactions

    Kussoy, M.I. / Horstman, K.C. / Horstman, C.C. | Tema Archive | 1993



    Crossing shock wave-turbulent boundary layer interactions

    NARAYANSWAMI, N. / KNIGHT, D. / BOGDONOFF, S. et al. | AIAA | 1991