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. (DePo)


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    Title :

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


    Additional title:

    Wirkung der Reynolds Zahl auf die Wechselwirkung von Schockwellen und turbulenten Grenzschichten bei transsonischen Stroemungen


    Contributors:
    Vidal, R.J. (author) / Wittclift, C.E. (author) / Cathin, P.A. (author) / Sheen, B.H. (author)

    Published in:

    Publication date :

    1973


    Size :

    17 Seiten


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English