Abstract: An unexpectedly high augmentation of aerodynamic lift for a given amount of power in STOL operation of a V/STOL aircraft is achieved by combining the unique features of a lifting body with those of a "jet flap", i.e. an aerodynamic mechanism in which a slipstream is directed over a deflected flap. Specifically, a movable flap is located on the trailing edge of the lifting body, and a tiltable propeller, which propels the aircraft in the normal manner in cruising, may be tilted, in low-speed flight, in order to direct air toward the leading edge of the flap and over the upper surface thereof. The movement of a large mass of air at a higher velocity over the upper surface of the flap maintains the air flow over the flap in an attached condition, and entrains and energizes the lower-velocity boundary layer on the airfoil forward of the flap, thereby producing an augmentation in lift.

Abstract: Fore mounted aft swept and aft mounted forward swept wings extend from either side of a lifting body fuselage. Each lateral pair of the wings is joined at the tops by a wing tip vortex translating device to induce translation of the tip generated vortices along the trailing edge of the aft wings. End plates extend rearwardly from the maximum chord thickness of the fuselage to increase the effective lift of the fuselage. An elevator, mounted intermediate the rear top of the end plates, provides pitch control and structurally augments the wing root and fuselage junction of the aft mounted wings. A power plant disposed at the rear of the fuselage provides thrust and also dissipates, as useful thrust, the wing tip vortices translated from the tips to the power plant along the trailing edges of the aft wings.

Abstract: A hybrid airfoil of extremely short span and thick chord section having a large portion of the trailing edge truncated with openings in the ends or side for air to enter and openings in the rear for the airflow to exit describing a flow pattern which resembles the letter "Y" within the airfoil for the express purpose of enhancing the performance of the short span truncated airfoil.

Abstract: Disclosed is an increased lift aircraft or similar device having an airfoil shaped forward structure. A mass flow engine, such as a jet engine, is positioned to the rear of this structure. In operation, the intake air flow for the engine flows around the forward structure, generating lift.

Abstract: Improvements in and relating to aircraft structures. The aircraft comprises a narrow delta planform fuselage with two small-span shoulder type wings in tandem and cascade. The shape of the fuselage and its relationship with the wings result in an aircraft capable of exploiting more efficiently, than conventional aircrafts, the potential energy carried by the aircraft and to comply more accurately with the first degree of universal flexibility as does the atmospheric environment than do conventional aircrafts.

Abstract: A jet thrust aircraft wing wherein the intake and exhaust are substantially coextensive with the leading and trailing edges, respectively; utilizing engine suction to induce intake of air and preventing build-up ahead of the wing by separating the same from the flow of air over and under the upper and lower wing surfaces; and utilizing engine exhaust thrust to induce controllable air flow through the wing and to induce longitudinal flow of air over and under the wing throughout its span.

Abstract: An aircraft which has a very low observability visually and to radar, thel and acoustic detecting devices. The aircraft is designed to have as few edges and surfaces as possible, such as a delta wing type, the edges being straight, or near straight and the vertices rounded. All surfaces are as near flat as possible, within the limits of aerodynamic requirements, and the entire surface of the aircraft is electrically conductive with minimum discontinuity. The propulsion unit is faired into and shielded from radar by the wing. Portions of the aircraft, particularly edges, may be of radar absorbing material, and any essential openings, ducts or protruding fins are similarly shielded to minimize the radar cross section.

Abstract: An aircraft having a composite configuration comprising a conventional fuselage forebody portion which symmetrically and variformly blends into a relatively wide, substantially flat beaver-tail-like afterbody, with the afterbody having an integral pitch trimming camber and a composite pitch control device and air brake, hinged transversely thereacross and forming at least a part of its trailing edge. The beaver-tail afterbody is geometrically blended into and joined with the after portion of the conventional forebody through the medium of an intervening medial body defined by a geometric transition piece. The composite aircraft is further capable of fixedly accommodating any type of conventional wing configuration without the necessity for any adaptative, structural change or modification and also carries conventional propulsion units and control surface components.