Patent ID: 8016233

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 shrouded turbofan engines, each engine with a nacelle mounted to the aircraft, each engine and nacelle completely and directly above the respective wing, strake, or a combination thereof, each nacelle including a leading end, a trailing end, a top, and a bottom; a vertical stabilizer mounted on each wing outboard of each respective outermost engine and nacelle at a vertical stabilizer mounting location; and 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, wherein the mounting location of each vertical stabilizer to the respective wing is lower than the bottom of the respective nacelle and each vertical stabilizer extends at least as high as the top of the respective nacelle, wherein the leading edge of each strake extends forward of the respective nacelle leading end 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 trailing end 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, the fuselage including a tail, and wherein forward, underneath, lateral, and aft shielding of engine noise and infrared radiation are provided.