A propulsive force imparted to an object is vectored using rotatable members arranged in one or more arrays disposed in the path of a fluid ejected by a fluid accelerator unit, such as air ejected by a fan driven by a gas turbine engine. The propulsive force is vectored by changing the rotation of one or more of the rotatable members.

The present invention belongs to the technical field of gas turbine engines used as propulsion systems for supersonic aircraft. In particular, the invention relates to thrust vectoring convergent-divergent nozzles and, more in particular, to an actuation mechanism for vectoring said variable geometry nozzle.

The present invention relates to an exhaust nozzle for fluidic-thrust vectoring, comprising an elongate channel for directing exhaust gasses having first and second ends. The elongate channel has an inlet at the first end comprising a continuous curved cross-sectional shape and an exit at the second end having a polygonal cross-sectional shape. In a preferred embodiment, the exhaust nozzle has a rectangular cross-sectional exit. A jet engine and an aircraft having the exhaust nozzle are also provided.