Download or read book An Experimental Investigation of Thrust Vectoring Two-Dimensional Convergent-Divergent Nozzles Installed in a Twin-Engine Fighter Model at High Angles of Attack written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 128 pages. Available in PDF, EPUB and Kindle. Book excerpt: An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine thrust vectoring capability of subscale 2-D convergent-divergent exhaust nozzles installed on a twin engine general research fighter model. Pitch thrust vectoring was accomplished by downward rotation of nozzle upper and lower flaps. The effects of nozzle sidewall cutback were studied for both unvectored and pitch vectored nozzles. A single cutback sidewall was employed for yaw thrust vectoring. This investigation was conducted at Mach numbers ranging from 0 to 1.20 and at angles of attack from -2 to 35 deg. High pressure air was used to simulate jet exhaust and provide values of nozzle pressure ratio up to 9. Capone, Francis J. and Mason, Mary L. and Leavitt, Laurence D. Langley Research Center AIRCRAFT ENGINES; CONVERGENT-DIVERGENT NOZZLES; FIGHTER AIRCRAFT; LONGITUDINAL CONTROL; THRUST VECTOR CONTROL; ANGLE OF ATTACK; FLAPS (CONTROL SURFACES); JET EXHAUST; NOZZLE GEOMETRY; PRESSURE RATIO; RESEARCH AIRCRAFT; WIND TUNNEL TESTS; YAW...