Three 50% flap configurations located inboard, outboard, and at midsemispan position were tested through momentum coefficient range from 0 to about 10 and angle of attack range from 10 to 28°; corresponding flow field characteristics are presented for longitudinal tail position of 4 wing chords behind trailing edge of wing through range of tail-height locatons of plus or minus 2 chords.


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    Title :

    Low-speed wind-tunnel investigation of reflection plane wing model equipped with partial-span jet-augmented flaps


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    53 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :