The present invention provides an improved Fluidic Thrust Vector Control Device for vectoring the exhaust jet in both pitch and yaw planes using secondary injection along the periphery of a non-circular primary nozzle geometry that is operating at high subsonic Mach numbers of 0.7-0.9.The secondary air is injected through converging nozzles placed all along the periphery of the nozzle. Small length straight deflector plates inclined at 15 degree  to the nozzle axis are connected to the outward side of the secondary nozzle exit forming an expansion corner. The secondary jet on encountering the corner expands and develops along this deflector plate directed away from the primary jet. The deflected secondary jet pulls the primary jet towards itself, locally accelerating it to supersonic velocities about the corner, and resulting in thrust vectoring. This device results in deflection angles of 7 degree  in yaw and 13 degree  in pitch planes for MFR of 1.33% and 5.5%, respectively. Increasing the deflector plate angle from 15 degree  to 30 degree and its length from 0.3lDe to 0.43De helps to further increase the thrust vectoring angle in both yaw and pitch planes. A plurality of secondary nozzles and deflector plates can also be opted for selective injection of fluid in order to affect finer control of aircraft attitude.