Abstract: An aircraft propulsion system is provided which incorporates a flight maneuverable exhaust nozzle. In one embodiment, gas turbine engines are mounted on both sides of an aircraft fuselage, each engine having an exhaust duct partially defining an exhaust stream flow path. The duct transists from a substantially cylindrical diffuser section aft of the engine to a relatively high aspect ratio section proximate the trailing edge of the wing. Exhaust gases are expelled through a thrust vectorable nozzle which is contoured within the wing and which is adapted to increase wing lift through the concept of supercirculation. Maximum aerodynamic advantage is achieved by distributing the exhaust flow over a significant portion of the wing span at the trailing edge. Thrust augmentation is provided through use of a long, flat duct burner disposed within the high aspect ratio section proximate the exhaust nozzle thereby minimizing turning losses and cooling air requirements.