EFFECTS OF NOZZLE EXIT LOCATION AND SHAPE ON PROPULSION-INDUCED AERODYNAMIC CHARACTERISTICS DUE TO VECTORING TWIN NOZZLES AT MACH NUMBERS FROM 0.40 TO 1.2

摘要

An investigation has been conducted in the Langley 16-foot transonic tunnel to deter¬mine 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 mov¬ing 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°, and thrust coefficients up to 0.35. Nozzle deflection angle varied from 0° to 45°. 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 106 to 13.12 x 106.