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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    Titel :

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


    Beteiligte:
    S. E. Gudmundson (Autor:in) / L. Torngren (Autor:in)

    Erscheinungsdatum :

    1987


    Format / Umfang :

    207 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch