Lift and pitching-moment characteristics of an NACA 0006 airfoil are presented for various deflections of a 0.15-chord leading-edge flap and a 0.30-chord plain trailing-edge flap. Pressure-distribution data are presented in tabular form. The data were obtained at a Mach number of 0.15 and a Reynolds number of 4,500,000.


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    Title :

    Section Characteristics of the NACA 0006 Airfoil with Leading-edge and Trailing-edge Flaps


    Contributors:

    Publication date :

    1956-12-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English