Aircraft Ground Test and Subscale Model Results of Axial Thrust Loss Caused by Thrust Vectoring Using Turning Vanes

Johnson, Steven A. (1992) Aircraft Ground Test and Subscale Model Results of Axial Thrust Loss Caused by Thrust Vectoring Using Turning Vanes. Technical Report NASA TM-4341, Research Engineering, NASA Dryden Flight Research Center.

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Abstract

The NASA Dryden Flight Research Facility 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 25º 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 square inches. The findings 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.

EPrint Type:	NASA Technical Memorandum
Keywords:	Axial thrust loss, Cold-jet nozzle, F/A-18 HARV, Jet exhaust turning vanes, Thrust vectoring
Subjects:	Aircraft/Project: F-18 HARV (01 - 09) Aeronautics: (05) Aircraft Design, Testing And Performance
ID Code:	272
Deposited On:	26 July 2004
Additional Information:	29 pages.