A new wing concept which lowers the inviscid drag of a wing in supersonic flow is described. The thrust-wing concept uses a secondary shock that occurs to the rear of the maximum thickness location to produce a significant aerodynamic thrust force from the rearward portion of the wing, thus reducing the inviscid drag. The evaluation of the thrust-wing concept is conducted on a delta-wing planform of differing sweep angles and thicknesses at Mach 1.60 over a wide range of lifting conditions.


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    Titel :

    Shock-dependent, thrust wings for supersonic flow


    Beteiligte:

    Kongress:

    AIAA, Aerospace Sciences Meeting and Exhibit ; 1993 ; Reno, NV, United States


    Erscheinungsdatum :

    01.01.1993


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :




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    Supersonic wings with significant leading-edge thrust at cruise

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