Wind-tunnel tests have been conducted at Mach numbers from 0.60 to 0.81 to determine the effects of trailing-edge geometry on the aerodynamic characteristics of a NASA supercritical airfoil shape. Variations in trailing-edge thicknesses from 0 to 1.5 percent of the chord and a cavity in the trailing edge were investigated with airfoils with maximum thicknesses of 10 and 11 percent of the chord.


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    Title :

    Wind-Tunnel Investigation of Effects of Trailing-Edge Geometry on a NASA Supercritical Airfoil Section


    Contributors:

    Publication date :

    1971


    Size :

    79 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English