Patent ID: 8628040

Claim:
A non-blended wing body aircraft comprising: a tubular fuselage; two wings with two wing strakes mounted to the tubular fuselage, the wings and strakes in a substantially delta wing configuration and each including a leading edge and a top surface, the wings each including a trailing edge; a plurality of nacelles mounted to the fuselage and having a leading end, a top, a bottom, and a longitudinal axis, each nacelle including a turbofan engine, a fan nozzle having a diameter, and a core nozzle, wherein each nacelle is completely and directly above the respective wing, strake, or a combination thereof; a substantially vertical stabilizer mounted on each wing outboard of each respective outermost nacelle at a mounting location; a split aft deck including a trailing edge and a multi-element upwardly rotatable pitch control surface including a trailing edge at the trailing edge of the deck, and noise shifting means associated with the core nozzle, the fan nozzle, or a combination thereof, of each nacelle, wherein the mounting location of each substantially vertical stabilizer to the respective wing is lower than the bottom of the respective outermost nacelle and each substantially vertical stabilizer extends at least as high as the top of the respective outermost nacelle, wherein the leading edge of each strake or wing, as applicable, extends forward of the respective nacelle leading end along the longitudinal axis of that nacelle at least a distance as great as the distance from the top surface of the respective wing to the top of the respective nacelle, wherein the trailing edge of the aft deck extends aft of the respective nacelle fan nozzle along the longitudinal axis of that nacelle at least a distance as great as the distance from the top surface of the respective wing to the top of the respective nacelle, wherein the fuselage extends between the nacelles and there is no central vertical stabilizer between the nacelles.