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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    Titel :

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


    Weitere Titelangaben:

    NASA -- Tech Note


    Beteiligte:


    Erscheinungsdatum :

    1961


    Format / Umfang :

    53 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :