Abstract: The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust.

Abstract: A bidirectional flying wing maximizes efficiency and reduces sonic boom during supersonic flight. The flying wing has bilateral symmetry across two perpendicular planes and a substantially isentropic compression bottom surface that minimizes the shock wave projected downward during flight. The flying wing may be rotated to provide a high aspect ratio and a low sweep angle during subsonic flight. The flying wing may be rotated to provide a low aspect ratio and a high sweep angle during supersonic flight.

Abstract: The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust.

Abstract: The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust rather than a conventional propulsion system (i.e., a propeller or jet engine).

Abstract: The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust.

Abstract: Airfoils are provided having non-monotonic meanline angle distributions and local negative camber along a length of the meanline between a point on a leading edge of the airfoil and a point on the trailing edge of the airfoil. The improved airfoil shape decreases the peak of a Mach number of a shock wave that develops in a passage between adjacent airfoils and attenuates or eliminates the shock wave at the suction surface of the airfoil within the passage. A blade constructed by this type of airfoil provides improved fluid flow in the passages between the airfoils, increased efficiency and an improved stall margin, among other benefits.

Abstract: A high efficiency forward swept airplane propeller includes a constant leading edge forward swept angle from the root to the tip. The forward sweep is created by leaning the blade leading edge tangentially toward the rotating direction on the rotating plane. The leading edge projection on the axial-radial plane is a straight line with constant axial position from the blade root to the tip. Alternate embodiments of the projection of the leading edge on the tangential rotating plane include: a propeller blade with a leading edge shape that has a smaller forward sweep angle (including 0 degree) in the inner portion of the blade and a larger forward sweep angle in the outer portion; a propeller blade that has a negative leading edge aft ward sweep angle in the inner portion of the blade and a positive forward sweep angle in the outer portion.