An investigation was conducted in the static test facility of the Langley 16-Foot Transonic Tunnel to determine the flow-turning capability and the nozzle internal performance of an axisymmetric convergent-divergent nozzle with post-exit vanes installed for multiaxis thrust vectoring. The effects of vane curvature, vane location relative to the nozzle exit, number of vanes, and vane deflection angle were determined. A comparison of the post-exit-vane thrust-vectoring concept with other thrust-vectoring concepts is provided. All tests were conducted with no external flow, and nozzle pressure ratio was varied from 1.6 to 6.0.


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    Title :

    Static Performance of an Axisymmetric Nozzle with Post-Exit Vanes for Multiaxis Thrust Vectoring


    Contributors:
    B. L. Berrier (author) / M. L. Mason (author)

    Publication date :

    1988


    Size :

    54 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English