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.


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    Title :

    Pressure distribution on a vectored-thrust V/STOL fighter in the transition-speed range


    Contributors:

    Publication date :

    1974-03-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :