Four thin airfoils (t/c = 0.05) were investigated experimentally. The aerodynamic efficiency of three supercritical airfoils is compared with that of a conventional one. The investigation was conducted in a transonic wind tunnel within a Mach number range of 0.6 to 0.95 and at Reynolds numbers 4 million to 6 million. Results show the superiority of supercritical airfoil design. This is explained, referring to overall aerodynamic coefficients, limits of efficiency, and in special cases to pressure distributions.


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    Title :

    Wind Tunnel Investigations on Thin Supercritical Airfoils in High Subsonic Flow


    Contributors:

    Publication date :

    1982


    Size :

    63 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English