The Langley V/STOL tunnel was used to determine the effects of vectoring exhaust flow on the longitudinal aerodynamic characteristics of a vectored-engine-over-wing configuration. Vectoring was accomplished by blowing from over-wing-mounted engines over a variable trailing-edge flap. Effects of varying canard geometry and wing leading-edge geometry were investigated. Wind-tunnel data were obtained at a Mach number of 0.186 for an angle-of-attack range from -20 deg to 24 deg and engine nozzle pressure ratios from 1.0 (jet off) to approximately 3.75.


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    Title :

    Longitudinal Aerodynamic Characteristics of a Vectored-Engine-over-Wing Configuration at Subsonic Speeds


    Contributors:

    Publication date :

    1979


    Size :

    136 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English