Preliminary wind tunnel tests of flap arrangements suitable for direct and immediate control of steepness of glide path of airplane; use for which present flaps are not satisfactory; arrangement giving maximum lift coefficient of 1.90 for all flap deflections between 25° and 80°, within which range drag of wing increased regularly to large value.


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    Title :

    Wind-tunnel tests of wing flaps suitable for direct control of glide-path angle


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Notes


    Contributors:
    Weick, F.E. (author)


    Publication date :

    1936


    Size :

    5 pages


    Remarks:

    12 Supp sheets


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English