An airfoil is examined that has an upper surface shaped to control flow accelerations and pressure distribution over the upper surface and to prevent separation of the boundary layer due to shock wave formulation at high subsonic speeds well above the critical Mach number. A highly cambered trailing edge section improves overall airfoil lifting efficiency. Diagrams illustrating supersonic flow and shock waves over the airfoil are shown.


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    Title :

    Airfoil shape for flight at subsonic speeds


    Contributors:

    Publication date :

    1976-04-27


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English


    Keywords :




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