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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    Titel :

    Measured Pressure Distributions inside Nonaxisymmetric Nozzles with Partially Deployed Thrust Reversers


    Beteiligte:
    R. S. Green (Autor:in) / G. T. Carson (Autor:in)

    Erscheinungsdatum :

    1987


    Format / Umfang :

    43 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch






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