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...