Supercritical technology has been applied to the design of a forward-swept-wing fighter configuration, and an assessment has been made of the relative performance of forward versus aft sweep. The wing and canard for this forward-swept wing configuration were designed for transonic maneuver by the use of a transonic computational analysis method and a transonic design procedure. The computational method calculated the transonic flow over a canard-wing-fuselage combination so that the strong transonic induced-flow effects of the canard on the wing are taken into account. A model of this configuration was constructed and was tested in the Langley 16-Foot Transonic Tunnel. The transonic theory gave a reasonably good estimate of the wing pressure distributions at transonic maneuver conditions. Comparison of this configuration with an equivalent aft-swept wing configuration showed that, at a Mach number of 0.9 and a lift coefficient of 0.9, the two configurations have essentially the same drag. This forward-swept wing configuration was also found to have very good maneuver performance relative to the Rockwell International HiMAT highly-maneuverable aircraft configuration.


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    Title :

    A forward-swept wing configuration designed for high maneuverability by use of three-dimensional transonic theory


    Additional title:

    Nach vorne gewoelbte Fluegelkonstruktionen fuer hohe Maneuvrierbarkeit mit Hilfe der dreidimensionalen Ueberschalltheorie


    Contributors:
    Mann, M.J. (author) / Mercer, C.E. (author)

    Published in:

    AIAA-Papers ; Okt ; 1-10


    Publication date :

    1985


    Size :

    10 Seiten, 11 Bilder, 1 Tabelle, 26 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English