Experimental data for a series of three-dimensional shock wave/turbulent boundary-layer interaction flows at Mach 8.2 are presented. The test bodies, composed of sharp fins fastened to a flat plate test surface, were designed to generate flows with varying degrees of pressure gradient, boundary-layer separation, and turning angle. The data include surface pressure, heat transfer, and skin friction distributions as well as limited mean flowfield surveys in both the undisturbed and interaction regimes. The data were obtained for the purpose of validating computational models of these hypersonic interactions.


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    Title :

    Three-dimensional hypersonic shock wave/turbulent boundary-layer interactions


    Contributors:

    Published in:

    Publication date :

    1993-01-01



    Type of media :

    Miscellaneous


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