Effects of nozzle exit location and shape propulsion-induced aerodynamic characteristics due to vectoring twin nozzles at Mach numbers from 0.40 to 1.2

An investigation was conducted in the Langley 16-foot transonic tunnel to determine the induced lift characteristics of a vectored-thrust concept in which jet-exhaust nozzles were located in the fuselage at or near the wing trailing edge. The effects of moving twin rectangular nozzles rearward from the wing trailing edge and of round nozzles at the trailing edge only were studied at Mach numbers from 0.4 to 1.2, angles of attack up to 14 deg, and thrust coefficients up to 0.35. Nozzle deflection angle varied from 0 deg to 45 deg. Separate force balances were used to determine both total aerodynamic and thrust forces and thrust forces alone which allowed for a direct measurement of jet turning angle at forward speeds. The Reynolds number per meter varied from 8.20 x 1 million to 13.12 x 1 million