Wind tunnel tests made at 0.60 to 0.92 Mach, corresponding to 3.0×106 to 4.2×106 Re based on wing mean aerodynamic chord, and at angles of attack from -2° to 24°; strakes provided improvements in directional stability characteristics of wing fuselage configuration, reflected in characteristics of model in angle of attack range where losses in directional stability frequently occur.


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    Title :

    Effect of high subsonic speeds of fuselage forebody strakes on static stability and vertical-tail-load characteristics of complete model having delta wing


    Additional title:

    NASA -- Tech Note


    Contributors:


    Publication date :

    1961


    Size :

    32 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :