Calculation of flow angle immediately behind trailing edge of flat plate airfoil and airfoil with thickness, on basis of oblique shock and Prandtl-Meyer wave theory; deflection angle of flat plate airfoil at given Mach Number is shown to first order to vary as fourth power of angle of attack; mechanism of return of flow downstream of airfoil to free stream direction.


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    Title :

    Flow at rear of two-dimensional supersonic airfoil


    Additional title:

    J Aeronautical Sciences


    Contributors:
    Kahane, A. (author) / Lees, L. (author)

    Published in:

    Publication date :

    1948


    Size :

    4 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



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