Wind tunnel tests to determine effect of angle of attack on maximum lift at stall for half-wing models, and single engine, jet propelled aircraft


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    Title :

    A flight and wind tunnel investigation of the effect of angle-of-attack rate on maximum lift coefficient


    Contributors:
    Conner, F. (author) / Twomey, W. (author) / Willey, C. (author)

    Publication date :

    1965-10-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English