Publisher's Synopsis
A static (wind-off) test was conducted in the static test facility of the Langley 16-foot Transonic Tunnel to evaluate the vectoring capability and isolated nozzle performance of the proposed thrust vectoring system of the F/A-18 high alpha research vehicle (HARV). The thrust vectoring system consisted of three asymmetrically spaced vanes installed externally on a single test nozzle. Two nozzle configurations were tested: A maximum afterburner-power nozzle and a military-power nozzle. Vane size and vane actuation geometry were investigated, and an extensive matrix of vane deflection angles was tested. The nozzle pressure ratios ranged from two to six. The results indicate that the three vane system can successfully generate multiaxis (pitch and yaw) thrust vectoring. However, large resultant vector angles incurred large thrust losses. Resultant vector angles were always lower than the vane deflection angles. The maximum thrust vectoring angles achieved for the military-power nozzle were larger than the angles achieved for the maximum afterburner-power nozzle. Mason, Mary L. and Capone, Francis J. and Asbury, Scott C. Langley Research Center F-18 AIRCRAFT; NOZZLE EFFICIENCY; NOZZLE GEOMETRY; RESEARCH VEHICLES; STATIC TESTS; THRUST VECTOR CONTROL; WIND TUNNEL TESTS; AFTERBURNING; EFFECTS; JET VANES; NOZZLES; PRESSURE RATIO; STATIC THRUST; TRANSONIC WIND TUNNELS...
