An investigation was conducted in the Langley 16-Foot Transonic Tunnel at static conditions to measure the pressure distributions inside a nonaxisymmetric nozzle with simultaneous partial thrust reversing (50-percent deployment) and thrust vectoring of the primary (forward-thrust) nozzle flow. Geometric forward-thrust-vector angles of 0 and 15 deg. were tested. Test data were obtained at static conditions while nozzle pressure ratio was varied from 2.0 to 4.0. Results indicate that, unlike the 0 deg. vector angle nozzle, a complicated, asymmetric exhaust flow pattern exists in the primary-flow exhaust duct of the 15 deg. vectored nozzle.


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    Title :

    Measured Pressure Distributions inside Nonaxisymmetric Nozzles with Partially Deployed Thrust Reversers


    Contributors:
    R. S. Green (author) / G. T. Carson (author)

    Publication date :

    1987


    Size :

    43 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English






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