Static investigation of post-exit vanes for multiaxis thrust vectoring

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Static investigation of post-exit vanes for multiaxis thrust vectoring

Berrier, B.L. / Mason, M.L.

A test has been 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 axisymmetric and nonaxisymmetric nozzles with post-exit vanes installed for multiaxis thrust vectoring. The axisymmetric nozzle utilized for these tests was a convergent-divergent type with an expansion ratio of 1.48. Tests were also conducted on three different nonaxisymmetric or two-dimensional nozzle types: a two-dimensional covergent nozzle (expansion ratio of 1.0); a two-dimensional convergent-divergent nozzle (nominal expansion ratio of 1.07); and a two-dimensional convergent-divergent nozzle (nominal expansion ratio of 1.08) oitch vectored at -11.7 degrees. Each nonaxisymmetric nozzle type was investigated with exit aspect ratios (width of exit divided by height of exit) of 1.5, 2.5, and 4.0. The geometric parameters investigated for the axisymmetric nozzle installation were number of vanes, vane curvature, vane location relative to the nozzle exit, and vane deflection angle. The geometric parameters investigated for the nonaxisymmetric nozzle installation were vane planform, vane curvature, nozzle type, and nozzle exit aspect ratio. All tests were conducted at static (no external flow) conditions and nozzle pressure ratio was varied from 1.5 to 6.0 using high pressure air for propulsion simulation.