Refinements in a 10 percent thick supercritical airfoil produced improvements in the overall drag characteristics at normal force coefficients from about 0.30 to 0.65 compared with earlier supercritical airfoils which were developed for a normal force coefficient of 0.7. The drag divergence Mach number of the improved supercritical airfoil (airfoil 26a) varied from approximately 0.82 at a normal force coefficient to of 0.30, to 0.78 at a normal force coefficient of 0.80 with no drag creep evident. Integrated section force and moment data, surface pressure distributions, and typical wake survey profiles are presented.


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    Title :

    Aerodynamic Characteristics of an Improved 10-Percent-Thick NASA Supercritical Airfoil


    Contributors:

    Publication date :

    1974


    Size :

    137 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English