The effects or nonaxisymmetrical fuselage design for reducing the drag of a low-sonic-boom airplane an investigated by computational fluid dynamics (CFD) analyses and verified in wind-tunnel tests. The nonaxisymmetrical fuselage design, in which the upper side of a fuselage is designed for low drag whereas the lower side is designed for low sink boom, is applied to the design of a Mach 1.7 scaled supersonic experimental airplane. The designed airplane is compared with a low-drag airplane and a low-sonic-boom airplane with an nonaxisymmetrical fuselage. The CFD analyses show the nonaxisymmetrical fuselage design can significantly reduce the drag of a low-sonic-boom airplane with an axisymmetrical fuselage without losing its low-sonic-boom characteristics. The CFD results are verified by force and near-field pressure measurements in supersonic wind-tunnel tests.


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    Titel :

    Nonaxisymmetrical fuselage shape modification for drag reduction of low-sonic-boom airplane


    Weitere Titelangaben:

    Simultane Reduzierung des Strömungswiderstandes und des Überschallknalls durch eine asymmetrische Form des Flugzeugrumpfs


    Beteiligte:
    Makino, Y. (Autor:in) / Suzuki, K. (Autor:in) / Noguchi, M. (Autor:in) / Yoshida, K. (Autor:in)

    Erschienen in:

    AIAA Journal ; 41 , 8 ; 1413-1420


    Erscheinungsdatum :

    2003


    Format / Umfang :

    8 Seiten, 18 Bilder, 2 Tabellen, 10 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch