Patent attributes
An aircraft having a gas turbine engine with vectorable cold and hot nozzles. The aircraft is provided with a ducting in the wing which extends from an inlet facing downwards to an outlet in the upper surface of the wing directed rearwardly. The cold vectorable nozzles of the engine are designed so that they can be swung from a vertical downward position to provide vertical lift to a horizontal position directed rearwardly to produce forward thrust, to a position where they are directed upwardly and discharged into the ducting 24. In this way, the air discharged through the outlet of the ducting 24 enhances the aerodynamic lift produced by the wing at slower speeds by inducing the air flow over the wing. In addition, the forward component of the thrust produced in the ducting provides a forward thrust on the aircraft, whilst additional forward thrust is produced by swiveling the hot nozzles.
