The aeropropulsive characteristics of an advanced twin-engine fighter designed for supersonic cruise were investigated in the Langley 16-Foot Transonic Tunnel. The objective of this investigation were to evaluate the performance characteristics of advanced nonaxisymmetric nozzles installed in various nacelle locations, the effects of thrust-induced forces on overall aircraft aerodynamics, the trim characteristics, and the thrust reverser performance. The major model variables included nozzle power setting; nozzle duct aspect ratio; forward, mid, and aft nacelle axial locations; inboard and outboard underwing nacelle locations; and underwing and overwing nacelle locations. Thrust-vectoring exhaust nozzle configurations included a wedge nozzle, a two dimensional convergent-divergent nozzle, and a single-expansion ramp nozzle, each with deflection angles up to 30 deg. In addition to the nonaxisymmetric nozzles, an axisymmetric nozzle installation was also tested. The use of a canard for trim was also assessed.
Effects of Varying Podded Nacelle-Nozzle Installations on Transonic Aeropropulsive Characteristics of a Supersonic Fighter Aircraft
1983
337 pages
Report
Keine Angabe
Englisch