Investigation made to study possibility of preventing shock-induced separation on wing with plain flap through use of area suction, and hence of reducing drag of wing; data obtained at R of 2.9×106 for range of Mach numbers from 0.70 to 0.84 with different suction area configurations.


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    Title :

    Tests of area suction flap on NACA 64A010 airfoil at high subsonic speeds


    Additional title:

    NASA -- Tech Note


    Contributors:
    Smith, D.W. (author) / Walker, J.H. (author)


    Publication date :

    1960


    Size :

    43 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :