Transonic and supersonic wind tunnel tests investigated the loads on one wing panel and one control panel at different positions on schematic body-wing, body-tail, and body-wing-tail cruciform missile configurations for 0 and 45 deg roll position. The Mach number range was 0.7 to 3.0 and the angle of attack varied between minus 3 degrees and plus 24 degrees. The tail controls were tested at different angles from 0 deg to -20 deg with 5 deg steps. The result is given in diagram and tables. Interference coefficients and downwash figures were evaluated.


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    Title :

    Wind Tunnel Investigation of Wing and Control Panel Loads at Transonic and Supersonic Speeds on Some Schematic Cruciform Missile Configurations


    Contributors:

    Publication date :

    1987


    Size :

    207 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English