A study has been conducted to explore the use of existing aerodynamic techniques to design a new supersonic cruise wing for an existing fighter wind-tunnel model. In addition to the usual wing design constraints of lift, pitching moment, and minimum drag, a ground rule was imposed that the wing had to fit on the existing fuselage. Experimental wind-tunnel results were obtained for a camber design and a reference flat wing. The flat wing was also fitted with leading-edge flaps which approximate the cruise camber design. The experimental results indicate that significant improvements in supersonic cruise capability can be obtained by a new wing designed using existing supersonic aerodynamic techniques.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Design study results of a supersonic cruise fighter wing


    Beteiligte:
    Miller, D. S. (Autor:in) / Schemensky, R. T. (Autor:in)

    Kongress:

    American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1979 ; New Orleans, LA


    Erscheinungsdatum :

    1979-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Design study results of a supersonic cruise fighter wing

    MILLER, D. / SCHEMENSKY, R. | AIAA | 1979


    Subsonic maneuver capability of a supersonic cruise fighter wing concept

    Riebe, Gregory D. / Fox, Charles H., Jr. | NTRS | 1987



    Design evolution of a supersonic cruise strike-fighter

    HENDRICKSON, R. / GROSSMAN, R. / SCLAFANI, A. | AIAA | 1978