Abstract: The invention is a flying wing aircraft having a forward fuselage; an aft fuselage segment; a propulsion segments adapted to mate to the fuselage segments; a pair of wing segments adapted to mate with the propulsion segments. The invention further includes a center section adapted to fit between the forward and aft fuselage sections; the center section adapted to receive multiple compartment systems.

Abstract: The invention is an aircraft that includes a flying wing having a plurality of extendable flaps mounted on the trailing edge of the flying wing. A canard is mounted on the nose of said flying wing. A system is mounted in the flying wing for providing high pressure air over the canard and the flaps. A second system is provided for controlling the flow of air over the canard to provide pitch control of the aircraft.

Abstract: 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.