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.


    Access

    Access via TIB

    Check availability in my library

    Order at Subito €


    Export, share and cite



    Title :

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


    Additional title:

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


    Contributors:
    Makino, Y. (author) / Suzuki, K. (author) / Noguchi, M. (author) / Yoshida, K. (author)

    Published in:

    AIAA Journal ; 41 , 8 ; 1413-1420


    Publication date :

    2003


    Size :

    8 Seiten, 18 Bilder, 2 Tabellen, 10 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English