Method developed for estimating, for airfoil section at arbitrary angle of attack, drag divergence Mach number, and free stream Mach number at which abrupt supercritical drag rise starts.


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    Title :

    Study of flow changes associated with airfoil section drag rise at supercritical speeds


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1949


    Size :

    31 pages


    Remarks:

    Charts


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :