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.
Static Performance of an Axisymmetric Nozzle with Post-Exit Vanes for Multiaxis Thrust Vectoring
1988
54 pages
Report
No indication
English
Static investigation of post-exit vanes for multiaxis thrust vectoring
Tema Archive | 1987
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