Tests indicated that increasing aileron profile thickness from that of true contour to that of straight sided aileron would increase positively rate of change of aileron section hinge moment coefficient with both section angle of attack and aileron deflection, and would cause little change in hinge moment parameter for given rate of roll at low aileron deflections.


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    Title :

    Investigation of approximately 0.178-chord-thick NACA 6-series-type airfoil section equipped with sealed internally balanced 0.20-chord ailerons and with 0.05-chord tab


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1948


    Size :

    28 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :