Study is made to provide design information which would aid in prediction of turbulent separation for aerodynamic devices, such as compressor blades, flaps, spoilers, and diffusers; results show that Mach and Reynolds number, and model shape all are important variables.


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    Title :

    Experimental investigation of pressure rise required for incipient separation of turbulent boundary layers in two-dimensional supersonic flow


    Additional title:

    NASA -- Memo


    Contributors:
    Kuehn, D.M. (author)


    Publication date :

    1959


    Size :

    48 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :