Detailed measurements of flow fields associated with low-speed turbulent boundary layers were made for the 17% thick GA(W)-1 airfoil section at nominal angles of attack of 10 deg, 14 deg, and 18 deg, Reynolds number 2.2 x 10, and Mach number 0.13. The data include pressure and velocity surveys of the pre- and post-separated regions on the airfoil and the associated wake. The boundary layer characteristics including regions of separation on the airfoil are also presented.


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    Title :

    Experimental studies of flow separation and stalling on a two-dimensional airfoil at low speeds


    Contributors:

    Publication date :

    1975-07-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :