Abstract: A propulsion system for an aircraft having a fuselage and a wing with two nacelles disposed on opposite sides of the fuselage, each of the nacelles having a turbo fan therein with drive means connected thereto for air flow through the nacelle from a forward air inlet to air exit openings, the air flow within the nacelle divided into twi air streams, one of the air-streams being directed downwardly through a variable area forward chin nozzle provided with a cascade of vanes for directing the outflow in a desired direction with the other air stream exhausted through an aft nozzle of variable area at the aft outlet opening against a slotted flap system mounted aft of the aft nozzle against which the outflow from the aft nozzle is directed so that the two air streams provide pitch, roll and yaw control as well as balanced lift and propulsion utilizing controlled thrust modulation and vectoring for all regimes of flight from vertical takeoff and landing (VTOL) or short takeoff and landing (STOL) or a combination o