An experimental investigation has been conducted to determine wing-alone supersonic aerodynamic characteristics at high angles of attack. The family of wings tested varied in aspect ratio from 0.5 to 4.0 and taper ratio from 0.0 to 1.0. The wings were tested at angles of attack ranging from 0 to 60 deg and Mach numbers from 1.6 to 4.6. The aerodynamic characteristics were obtained by integrating local pressures measured over the wing surface. Comparison of these data with the limited available data from the literature indicate the present data are free of sting interference effects through the test range of angle of attack. Presented and discussed are results showing the effects of model geometry, Mach number and angle of attack on aerodynamic characteristics consisting of normal force, pitching moment, bending moment, longitudinal center-of-pressure locations, and lateral center-of-pressure locations.


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    Titel :

    Wing-alone aerodynamic characteristics at high angles of attack


    Beteiligte:
    Stallings, R. L., Jr. (Autor:in) / Lamb, M. (Autor:in)

    Kongress:

    Aerospace Sciences Meeting ; 1981 ; St. Louis, MO


    Erscheinungsdatum :

    1981-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Wing-alone aerodynamic characteristics at high angles of attack

    STALLINGS, JR., R. / LAMB, M. | AIAA | 1981


    Wing-Alone Aerodynamic Characteristics at High Angles of Attack

    Robert L. Stallings Milton Lamb | AIAA | 1982




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