A supersonic aircraft having retractable wings and stabilizer controls wherein the leading edge of the airfoil is a continuous air inlet and the fuselage and all remaining portions of the aircraft are situated largely downstream of the air inlet, the aircraft being substantially T-shaped in configuration, a large portion of the shock wave generated by the aircraft being received into the air inlet. At least a portion of the jet exhaust is deflected into the shock wave produced by the aircraft at supersonic speeds for the purpose of disrupting the shock wave. Rapid deceleration of the aircraft from supersonic to sonic speeds obtained by extension of retractable airfoils and stabilizers.