Wind tunnel investigation of conventional fighter airplane; results showed that minimum lift coefficient increased linearly with pitching velocity up to limit value of coefficient which depended on Mach number.


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    Title :

    Effect of rate of change of angle of attack on maximum lift of small model


    Additional title:

    Nat Advisory Committee Aeronautics -- Tech Note


    Contributors:


    Publication date :

    1950


    Size :

    20 pages


    Remarks:

    Illus, Diagrs, Charts


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :