A Ludwieg tube experiment is described in which the pertinent features of the shock wave-boundary layer interaction on an airfoil are simulated with a two-dimensional flat plate in a supersonic nozzle. The nozzle is modified to impress an airfoil pressure distribution on the flat plate that is typical of a cruising flight condition. A normal shock wave is positioned at a fixed location on the plate, and measurements are made in the vicinity of the shock wave-boundary layer interaction zone.


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    Title :

    Reynolds Number Effects on the Shock Wave-Turbulent Boundary Layer Interaction at Transonic Speeds


    Contributors:
    R. J. Vidal (author) / C. E. Wittliff (author) / P. A. Catlin (author) / B. H. Sheen (author)

    Publication date :

    1973


    Size :

    17 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Reynolds number effects on the shock wave-turbulent boundary layer interaction at transonic speeds

    Vidal, R.J. / Wittclift, C.E. / Cathin, P.A. et al. | Tema Archive | 1973




    A normal shock-wave turbulent boundary-layer interaction at transonic speeds

    Mateer, G. / Brosh, A. / Viegas, J. | Tema Archive | 1976