Current advanced fighter designs usually include a fuselage with chine-shaped cross section to minimize observables. The presence of the chines results in a fixed location of flow separation and generally stronger forebody vortices being shed than would be the case for a configuration with a smooth-sided forebody. These stronger vortices can be useful in that they can synergistically augment the lift over the main wing; however, these chine vortices can also lead to pitch up and nonlinearities in lateral stability due to windward vortex burst at sideslip. Consequently, vortices from chined forebodes can have a significant impact on both longitudinal and 1ateraL/directional stability. The present paper describes a portion of a joint NASA and U.S. Air Force study undertaken at the Langley Research Center to investigate the impact of chine-shaped fuselage cross section on the longitudinal and lateral/directional stability of a generic fighter model. The overall study involved a number of wind tunnel entries at subsonic and transonic speeds.


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    Titel :

    Impact of Fuselage Cross Section on the Stability of a Generic Fighter


    Beteiligte:
    R. M. Hall (Autor:in)

    Erscheinungsdatum :

    2004


    Format / Umfang :

    16 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch