A wind-tunnel investigation has been conducted to determine the exhaust-nozzle aerodynamic and propulsive characteristics for a twin-jet variable-wing-sweep fighter airplane model. The powered model was tested in the Langley 16-foot transonic tunnel and in the Langley 4-foot supersonic pressure tunnel at Mach numbers to 2.2 and at angles of attack from about minus 2 to 6 deg. Compressed air was used to simulate the nozzle exhaust flow at values of jet total-pressure ratio from approximately 1 (jet off) to about 21. Effects of configuration variables such as speed-brake deflection, store installation, and boundary-layer thickness on the the nozzle characteristics were also investigated. (Author)


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    Title :

    Exhaust-Nozzle Characteristics for a Twin-Jet Variable-Wing-Sweep Fighter Airplane Model at Mach Numbers to 2.2


    Contributors:

    Publication date :

    1974


    Size :

    137 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English