Wind tunnel investigations were conducted on a generic cruciform canard-controlled missile configuration. The model featured fixed or free-rolling tail-fin afterbodies to provide an expanded aerodynamic data base with particular emphasis on alleviating large induced rolling moments and/or for providing canard roll control throughout the entire test angle-of-attack range. The tests were conducted in the NASA Langley Unitary Plan Wind Tunnel at Mach numbers from 2.50 to 3.50 at a constant Reynolds number per foot of 2.00 × 106. Selected test results are presented to show the effects of a fixed or free-rolling tail-fin afterbody on the static longitudinal and lateral-directional aerodynamic characteristics of a canard-controlled missile with pitch, yaw, and roll control at model roll angles of 0° and 45°.


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    Titel :

    Supersonic Aerodynamic Characteristics of a Maneuvering Canard-Controlled Missile with Fixed and Free-Rolling Tail Fins


    Weitere Titelangaben:

    Sae Technical Papers


    Beteiligte:
    Blair, A. B. (Autor:in)

    Kongress:

    Aerospace Technology Conference and Exposition ; 1990



    Erscheinungsdatum :

    01.09.1990




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch