A summary of some results from tests of a wing-body general research missile model is presented for a Mach number range up to 4.63. A basic ogive-cylinder body with a length-to-diameter ratio of 10 was used to which was attached a series of wing planforms. The planforms included a family of delta wings and a family of rectangular wings having a constant root chord but varying spans so that wings of constant exposed area could be compared. In addition, a cranked-tip planform was included and a rectangular planform with reduced chord. Some results are presented for wing-body-tail configurations - one utilizing a cranked wing planform and one with wings having a constant root chord and span, but tip chords that were 0, 20, and 40 percent of the root chord.


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    Title :

    Effects of some geometric variations on missile aerodynamic characteristics at supersonic speeds


    Contributors:

    Conference:

    AIAA Aerospace Sciences Meeting ; 1986 ; Reno, NV, United States


    Publication date :

    1986-02-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :