AERODYNAMIC EFFECTS INDUCED BY A VECTORED HIGH ASPECT RATIO NON-AXISYMMETRIC EXHAUST NOZZLE

Nonaxisymmetric exhaust nozzles exiting at or near the trailing edge of a lifting surface offer advanced aircraft configurations improved performance because of induced aerodynamic effects. An experimental investigation of these induced effects was conducted at Mach numbers from 0.3 to 0.9 on a half-span wing body configuration with a high aspect ratio vectoring (0, 15, 30 deg) nonaxisymmetric exhaust nozzle incorporated into the wing trailing edge. Results indicate that, at all Mach numbers, the thrust-removed lift, drag, and pitching moment coefficients for the wing body increased with increasing nozzle vectoring. Using the trimmed data, an optimum drag polar can be formed which uses all three vector angles. As the nozzle pressure ratio increases, the induced effects on the wing aerodynamics tend to increase proportionally. © 1979 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.