Results of pressure-distribution tests on airfoil with conventional trailing edge flap, which were made in atmospheric wind tunnel; maximum chord loadings were obtained with flap displaced downward and with airfoil at large angles of attack; greater changes were produced in normal force and in center of pressure travel by upflap than by equal downflap displacement.


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    Title :

    Wind tunnel pressure distribution tests on an airfoil with trailing edge flap


    Additional title:

    Nat. Advisory Committee Aeronautics -- Tech. Note


    Contributors:


    Publication date :

    1929


    Size :

    10 pages


    Remarks:

    10 Figs., Bibliography


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :