Northrop Grumman Corpoation

Berry Thomas Gibson

Heinz A Gerhardt

James Franklin Kerswell

Richard Thomas Priestley

The present invention is a laminar supersonic transport aircraft having a reverse delta wing located between a forward section and a distal end of the aircraft, a set of jet engines superposed on another set of jet engines, a stabilizing vertical tail located near the distal end of the aircraft, a stabilizing canard surface located near the forward section of said aircraft. Also, a laminar flow control device can be incorporated within the wing. The reverse delta aerodynamic wing has a basic reverse delta wing portion bounded by a leading edge and by a pair of trailing edges extending from respective ends of the leading edge toward a trailing apex point and respective span-wise wing extensions in a natural laminar boundary layer wing region extending chordwise from the leading edge by a fraction of the chordlength of the wing and extending span-wise from opposing sides of said wing.

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Kennesaw, GA, United States of America

Berry Thomas Gibson