Aircraft Ground Tests And Subscale Model Results Of Axial Thrust Loss Caused By Thrust Vectoring Using Turning Vanes
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Aircraft Ground Tests and Subscale Model Results of Axial Thrust Loss Caused by Thrust Vectoring Using Turning Vanes
The NASA Dryden Flight Research Center F/A-18 high alpha research vehicle was modified to incorporate three independently controlled turning vanes located aft of the primary nozzle of each engine to vector thrust for pitch and yaw control. Ground-measured axial thrust losses were compared with the results from a 14.25 percent cold-jet model for single- and dual-vanes inserted up to 25° into the engine exhaust. Data are presented for nozzle pressure ratios of 2.0 and 3.0 and nozzle exit areas of 253 and 348 in2. The results of this study indicate that subscale static nozzle test results properly predict trends but underpredict the full-scale results by approximately 1 to 4.5 percent in thrust loss.