| 摘要 |
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.
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