A wind-tunnel investigation has been conducted in the Langley V/STOL tunnel with a vectored-thrust V/STOL fighter configuration to obtain detailed pressure measurements on the body and on the wing in the transition-speed range. The vectored-thrust jet exhaust induced a region of negative pressure coefficients on the lower surface of the wing and on the bottom of the fuselage. The location of the jet exhaust relative to the wing was a major factor in determining the extent of the region of negative pressure coefficients. (Author)


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Pressure Distribution on a Vectored-Thrust V/STOL Fighter in the Transition-Speed Range


    Beteiligte:
    R. E. Mineck (Autor:in) / R. J. Margason (Autor:in)

    Erscheinungsdatum :

    1974


    Format / Umfang :

    398 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch