Determinations of the power-off maximum lift of a Fairchild 22 airplane were made in the NACA full-scale wind tunnel and in flight. The results from the two types of test were in satisfactory agreement. It was found that, when the airplane was rotated positively in pitch through the angle of stall at rates of the order of 0.1 degree per second, the maximum lift coefficient was considerably higher than that obtained in the standard tests, in which the forces are measured with the angles of attack fixed. Scale effect on the maximum lift coefficient was also investigated.


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    Title :

    Comparative Flight and Full-Scale Wind-Tunnel Measurements of the Maximum Lift of an Airplane


    Contributors:

    Publication date :

    1938-01-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English



    Comparative flight and full-scale wind-tunnel measurements of maximum lift of airplane

    Silverstein, A. / Katzoff, S. / Hootman, J.A. | Engineering Index Backfile | 1938


    Comparative flight and full-scale wind tunnel measurements of maximum lift of airplane

    Silverstein, A. / Katzoff, S. / Hootman, J.A. | Engineering Index Backfile | 1938


    Comparative flight and full-scale wind-tunnel measurements of maximum lift of airplane

    Silverstein, A. / Katzoff, S. / Hootman, J.A. | Engineering Index Backfile | 1938


    Comparative flight and full-scale wind-tunnel measurements of the maximum lift of an airplane

    Silverstein, Abe / Katzoff, S. / Hootman, James A. | TIBKAT | 1938