A theoretical and experimental investigation was conducted of the subsonic maneuver capability of a fighter wing concept designed for supersonic cruise. To improve the subsonic maneuver capability, the wing utilized full-span leading- and trailing-edge flaps that were designed with the aid of a subsonic-analysis computer program. Wind-tunnel tests were made at Mach numbers of 0.3, 0.5, and 0.7. Force and moment data obtained were compared with theoretical predictions of Mach 0.5 from two subsonic-analysis computer programs. The two theoretical programs gave a good prediction of the lift and drag characteristics but only a fair prediction of the pitching moment. The experimental results of this study show that with the proper combination of leading- and trailing-edge flap deflections, a suction parameter of nearly 90 percent can be attained at a Mach number of 0.5 and a lift coefficient of 0.73; this is a three-fold improvement from 30 percent for the basic wing.


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    Titel :

    Subsonic Maneuver Capability of a Supersonic Cruise Fighter Wing Concept


    Beteiligte:
    G. D. Riebe (Autor:in) / C. H. Fox (Autor:in)

    Erscheinungsdatum :

    1987


    Format / Umfang :

    74 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch