A wind-tunnel free-flight investigation was conducted to study the dynamic stability characteristics of a model of a forward-swept-wing fighter-airplane configuration at high angles of attack. Various other wind-tunnel techniques employed in the study included static- and dynamic- (forced-oscillation) force tests, free-to-roll tests, and flow-visualization tests. A unique facet of the study was the extreme level of static pitch instability (in excess of negative 32-percent static margin) inherent in the airframe design which precluded free-flight testing without stability augmentation in pitch. Results are presented which emphasize the high-angle-of-attack aerodynamics and the vehicle-component contributions to these characteristics. The effects of these aerodynamic characteristics on the high-angle-of-attack flying qualities of the configuration are discussed in terms of results of the wind-tunnel free-flight tests.


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    Titel :

    Wind-Tunnel Free-Flight Investigation of a Model of a Forward-Swept-Wing Fighter Configuration


    Beteiligte:
    D. G. Murri (Autor:in) / L. T. Nguyen (Autor:in) / S. B. Grafton (Autor:in)

    Erscheinungsdatum :

    1984


    Format / Umfang :

    71 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch





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