Abstract: This invention outlines excitation means to transform the linear momentum of an underwing energized jet into rotational form in a selective manner to provide an asymmetric shear layer to increase compression wave reflection from the forward undersurface of a supersonic wing. The wing compression energy is thereby recovered into useful work as an increase in pressure on the upward reflexed wing backside. The upper surface of the shear layer is comprised of an array of vortices whose rotation is opposite to the wing circulation, providing the required angular momentum reaction. The upper wing surface is flat to avoid generation of waves and an adverse angular momentum reaction above the wing. The vortices below the wing are compressed by the underwing pressure, comprising a pressure shield to enhance the reflection.

Abstract: This invention is an improvement of my system for supersonic aircraft which provides the required angular momentum reaction to the continuous generation of new lift circulation by vorticity in lieu of dissipative shock waves. This new system relocates the propulsive jet forward utilizing its excess energy to generate this vorticity in a planar sheet below the wing acting as a pressure shield, which continues downstream beyond the wing trailing edge as a vortex flap simulating an extended wing chord. The present invention provides mechanical vortex generating means to augment this free surface mechanism in cases where the jet velocity is insufficient. This invention also incorporates a wide-body fuselage above this pressure shield, and provides further system improvement in propulsion/wing integration.

Abstract: This invention is an extension of my system to recover into useful work the energy normally wasted by a supersonic aircraft in its shock wave mechanism. This system utilizes the excess propulsive jet velocity in a sheet below the wing to form a planar vortex flap which acts as a pressure shield. The present improvement extends the pressure generating forward concave wing undersurface of this system into an upward reflexed aft surface so as to benefit from the increased pressure provided by the downstream upwash vortex field. This allows the aft portion of the wing to serve as the energy recovery section by achieving the pressure required for lift on the undersurface of this aft wing portion at a lesser angle with reduced drag. This stream-wise series of functions specifies the wing undersurface as concave, convex, and concave sequentially in the flow direction, thus corresponding to the upper element of a planar supersonic nozzle.