An aircraft (101; 1001), comprising: an engine exhaust duct; a nozzle assembly (401; 1018) rigidly attached to and concentrically aligned with the engine exhaust duct, the nozzle assembly (401; 1018) having a first nozzle (403, 405, 407) and a second nozzle (403, 405, 407) in gaseous communication with the engine exhaust duct, the first nozzle (403, 405, 407) being configured to redirect engine exhaust gas in a different direction relative to redirected gas from the second nozzle (403, 405, 407); a rotatable valve disposed within the nozzle assembly (401; 1018), the valve being configured to rotate concentrically to the engine exhaust duct, the rotatable valve having: a scoop portion in gaseous communication with the engine exhaust duct, the scoop portion being configured to redirect all engine exhaust gases leaving the engine exhaust duct to the first nozzle (403, 405, 407) and/or the second nozzle (403, 405, 407); wherein the scoop is selectively contoured to reduce turbulent flow as the exhaust gas is channelled from the exhaust duct to the first nozzle (403, 405, 407) and/or the second nozzle (403, 405, 407); a wing extension carried within a wing (107; 1007) of the aircraft, the wing extension being configured to extend from the wing (107; 1007) in an extended position and retract within the wing while in a retracted position. an engine exhaust duct; a nozzle assembly (401; 1018) rigidly attached to and concentrically aligned with the engine exhaust duct, the nozzle assembly (401; 1018) having a first nozzle (403, 405, 407) and a second nozzle (403, 405, 407) in gaseous communication with the engine exhaust duct, the first nozzle (403, 405, 407) being configured to redirect engine exhaust gas in a different direction relative to redirected gas from the second nozzle (403, 405, 407); a rotatable valve disposed within the nozzle assembly (401; 1018), the valve being configured to rotate concentrically to the engine exhaust duct, the rotatable valve having: a scoop portion in gaseous communication with the engine exhaust duct, the scoop portion being configured to redirect all engine exhaust gases leaving the engine exhaust duct to the first nozzle (403, 405, 407) and/or the second nozzle (403, 405, 407); wherein the scoop is selectively contoured to reduce turbulent flow as the exhaust gas is channelled from the exhaust duct to the first nozzle (403, 405, 407) and/or the second nozzle (403, 405, 407); a wing extension carried within a wing (107; 1007) of the aircraft, the wing extension being configured to extend from the wing (107; 1007) in an extended position and retract within the wing while in a retracted position. a scoop portion in gaseous communication with the engine exhaust duct, the scoop portion being configured to redirect all engine exhaust gases leaving the engine exhaust duct to the first nozzle (403, 405, 407) and/or the second nozzle (403, 405, 407); wherein the scoop is selectively contoured to reduce turbulent flow as the exhaust gas is channelled from the exhaust duct to the first nozzle (403, 405, 407) and/or the second nozzle (403, 405, 407); a wing extension carried within a wing (107; 1007) of the aircraft, the wing extension being configured to extend from the wing (107; 1007) in an extended position and retract within the wing while in a retracted position.