NASA NTRS · 19870057962
Static investigation of post-exit vanes for multiaxis thrust vectoring
Abstract
Transonic wind tunnel tests are conducted to determine the flow-turning capabilities and nozzle internal performance of axisymmetric and nonaxisymmetric nozzles employing postexit vanes for multiaxis thrust-vectoring. The geometric parameters investigated for the axisymmetric nozzle installation were number of vanes, vane curvature, vane location relative to nozzle exit, and vane deflection angle; for the nonaxisymmetric cases, the parameters were vane planform and curvature, nozzle type, and nozzle exit aspect ratio. Nozzle pressure ratio was varied from 1.5 to 6.0, using high pressure air.
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Berrier, Bobby L., Mason, Mary L.. 1987-06-01. Static investigation of post-exit vanes for multiaxis thrust vectoring. https://ntrs.nasa.gov/citations/19870057962
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