Study is undertaken to determine effects of leading edge flap deflection and boundary layer control on maximum lift and longitudinal stability; lift, drag, and pitching moment are measured at Reynolds number of 8.2 million for various combinations; model conformed to that of F-100 aircraft.


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    Title :

    Low-speed wind-tunnel investigation of blowing boundary-layer control on leading- and trailing-edge flaps of large-scale, low-aspect-ratio, 45° swept-wing airplane configuration


    Additional title:

    NASA -- Memo


    Contributors:
    Maki, R.L. (author)


    Publication date :

    1959


    Size :

    25 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :