Method enables determination of form and magnitude of incremental normal force distribution to be made for airfoil flap combination for which section characteristics have been determined.


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    Title :

    Calculation of chordwise load distribution over airfoil sections with plain, split, or serally hinged trailing-edge flaps


    Additional title:

    Nat Advisory Committee Aeronautics -- Report


    Contributors:
    Allen, H.J. (author)


    Publication date :

    1938


    Size :

    16 pages


    Remarks:

    Bibliography


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :