Wind tunnel tests were conducted on the NASA LS(1)-0421 Mod, NACA 2412 and NASA GA(W)-2 airfoil sections at a Reynolds number of 2.2 x 10(6) and a Mach number of 0.13. Detailed measurements of flow fields associated with turbulent boundary layers of these airfoils were obtained at pre-stall, near-stall, and post-stall angles of attack. Velocity and pressure survey results over the airfoil and in the associated wake, are presented for fully attached flow conditions through the stalled flow condition. Extensive force, pressure, tuft survey, hot-film survey, local skin friction and boundary layer data are also included.


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    Titel :

    Experimental Studies of Flow Separation of Three Airfoils at Low Speeds


    Beteiligte:
    E. J. Rodgers (Autor:in) / H. C. Seetharam (Autor:in) / W. H. Wentz (Autor:in)

    Erscheinungsdatum :

    1982


    Format / Umfang :

    164 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Experimental studies of flow separation of three airfoils at low speeds

    Rodgers, E. J. / Seetharam, H. C. / Wentz, W. H., Jr. | NTRS | 1982



    Airfoils at low speeds

    Selig, Michael S. / Donovan, John F. / Fraser, David B. | TIBKAT | 1989



    Studies of Flow Separation and Stalling on One- and Two-Element Airfoils at Low Speeds

    Seetharam, H. C. / Wentz, W. H. | SAE Technical Papers | 1977