This report deals with pressure distribution tests on an airfoil with a conventional trailing edge flap. These tests were conducted in the Atmospheric Wind Tunnel of the National Advisory Committee for Aeronautics. Maximum chord loadings were obtained with the flap displaced downward and with the airfoil at large angles of attack. Greater changes were produced in the normal force and in the center of pressure travel by up-flap than by an equal down-flap displacement.


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    Title :

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


    Contributors:

    Publication date :

    1929-10-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English