A steady-state computational fluid dynamic (CFD) study is made of the flowfield in the vicinity of a jet-vane mounted at the exit of a rocket nozzle. Vane deflection angles of 0, 10, and 20 degrees are considered. Surface stresses on the jet-vane and its mount are integrated. Computed thrust vecotr control (TVC) forces are obtained. Satisfactory agreement is found when compared to Static hot-fire test results for the same configuraiton.
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