Investigation in stability tunnel showed that fuselage experienced large increase in yawing moment as angle of attack increased, owing to asymmetrical disposition of pair of trailing vortices emanating from noise.


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    Title :

    Low-speed experimental study of directional characteristics of sharp-nosed fuselage through large angle-of-attack range at zero angle of slideslip


    Additional title:

    NACA -- Tech Note


    Contributors:
    Letko, W. (author)


    Publication date :

    1953


    Size :

    27 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :