Abstract: This invention is an airfoil which has particular application to the blade or blades of rotor aircraft and aircraft propellers. The airfoil thickness distribution, camber and leading edge radius is shaped to locate the airfoil crest at a more aft position along the chord, and to increase the freestream Mach number at which sonic flow is attained at the airfoil crest. The upper surface of the airfoil has a general reduction in the surface slope back to the maximum ordinate which is about 40 percent of the airfoil chord. The reduced slope causes a reduction in velocity at the airfoil crest at lift coefficients from zero to the maximum lift coefficient. The leading edge radius is adjusted or shaped so that the maximum local Mach number at 1.25 percent chord and at the designed maximum lift coefficient is limited to about 0.48 when the Mach number normal to the leading edge is approximately 0.20.

Abstract: A multi-purpose mono-element airfoil is disclosed for aerodynamic vehicles and devices. The multi-purpose mono-element highlift airfoil when utilized in an aerodynamic application provides a combined no-moving-parts high lift and cruise airfoil which in conjunction with a plenum, upon pressure initiation, causes pressurized air to issue from a slot tanget to the airfoil surface and remains attached to the airfoil's shaped trailing edge, providing a controlled resultant force or thrust. Upon application to hydrodynamic vehicles, the multi-purpose mono-elements airfoil is placed in the freestream and provides turning or pitching forces to the vehicle without any deflection of itself or any mechanical components.

Abstract: The supercritical profile has an upper surface whose curvature has two minima, one in front of the mid-chord station, the other one rather close to the trailing edge and having a lower value than the first one. The curvature of the lower surface remains larger beyond the mid-chord station, changes sign and increases to a pronounced maximum not far from the second curvature minimum of the upper surface, and drops to zero at the trailing edge.

Abstract: A low drag surface comprises at its upstream edge an intermittent linear vortex producing means extending transverse to the flow of fluid across the surface. The vortex producing means produces a succession of rolling vortices which roll across the surface reducing the drag between the main flow and the surface.

Abstract: The present invention relates to a blade section for rotating wings of an aircraft comprising, between the leading edge and the trailing edge, a convex lower surface and an upper surface which is convex over the greater part of its length, but concave near the trailing edge. According to the invention, the upper surface of the section comprises a region of small extent, close to the leading edge but not contiguous thereto, in which the curvature is substantially constant. The invention is applicable to the improvement of the performances in maneuvering flight, while hovering and in advance flight of the aircraft.

Abstract: The invention relates to an airfoil shape for flight at high subsonic speeds, of the type comprising a flat convex upper surface, a thick leading edge and a lower surface convex towards the leading edge and concave towards the trailing, in which airfoil the upper surface comprises a maximum curvature in the vicinity of its rear part, in a zone delimited by points located at distances from the leading edge equal to 65 and 90% of the chord of the airfoil. The invention is applicable to the production of fixed or rotary wings for aircraft, having a high divergence Mach number and a low drag.

Abstract: This invention is an airfoil which has particular application to the blade or blades of rotor aircraft such as helicopters and aircraft propellers. The airfoil thickness distribution and camber are shaped to maintain a near zero pitching moment coefficient over a wide range of lift coefficients and provide a zero pitching moment coefficient at section Mach numbers near 0.80 and to increase the drag divergence Mach number resulting in superior aircraft performance.

Abstract: A toy sailplane having a single piece sweptback wing that is symmetrical with respect to a central plane is disclosed. The wing has a central nose and two leading edges extending in obtuse angular relation from the nose. The wing includes a wing tip portion located at the end of each leading edge that is upwardly directed to provide flight stability. The wing also includes a trailing edge extending between the tip portions. A weight is suspended from the wing at a location on the central plane intermediate the nose and the trailing edge, the weight preferably being longitudinally adjustable to vary the center of gravity of the sailplane and the angle of attack of the wing.

Abstract: A multi-purpose mono-element airfoil is disclosed for aerodynamic and hydrodynamic vehicles and devices. The multipurpose mono-element highlift airfoil when utilized in an aerodynamic application provides a combined no-moving-parts high lift and cruise airfoil which in conjunction with a plenum, upon pressure initiation, causes pressurized air to issue from a slot tangent to the airfoil surface and remains attached to the airfoil's shaped trailing edge, providing a controlled resultant force of thrust. Upon application to hydrodynamic vehicles, the multi-purpose mono-element airfoil is placed in the freestream and provides turning or pitching forces to the vehicle without any deflection of itself or any mechanical components.

Abstract: Modifications to a jet aircraft of the type having aft fuselage-mounted engine nacelles overlapping trailing edge portions of the aircraft's wings, wherein a channel area defined by the fuselage, wing, pylon and attached nacelle is shaped to prevent air flowing therethrough from forming a shock wave during flight operation in the transonic regime, resulting in significant drag reduction as compared to an unmodified jet aircraft of a similar type. Further modifications to the jet aircraft's wings provide additional lift while significantly reducing drag as compared to a similar, unmodified aircraft. The present invention is particularly adaptable for use with Gates Learjet type aircraft, especially Models 23, 24, 25 and other models having similar nacelle, pylon and inboard wing arrangements.

Abstract: A thin, high performance swept wing of the tapered type with an improved leading edge characterized by a first portion that extends from near the wing root at a fixed radius to a transition point where twice the fixed radius does not exceed about 100.6 percent of wing thickness at about 5 percent of the local chord at the transition point, and a second leading edge portion extending from the transition point to the wing tip that has a radius expressed in percent of local chord which does not exceed that percent of local chord at the transition point. Winglets are optionally provided in combination with the wing with improved leading edge to provide in combination, improved aircraft performance.

Abstract: The invention relates to a high performance aerodynamic airfoil for aircraft wing, wherein the airfoil is biconvex and is such that the corresponding wing comprises an advanced maximum total thickness and at least substantially zero curvature over the major part of the airfoil surfaces of the upper surface and lower surface, downstream of the maximum total thickness, the point of maximum thickness of the lower surface being nearer the leading edge than the point of maximum thickness of the upper surface. The invention finds particular application to the manufacture of fixed or rotary wings of aircraft.

Abstract: A toy flying object consists of a single wing which is shaped and weighted to provide aerodynamic capabilities. The single wing structure is readily and simply manufactured.

Abstract: This invention is an extension of my system to recover into useful work the energy normally wasted by a supersonic aircraft in its shock wave mechanism. This system utilizes the excess propulsive jet velocity in a sheet below the wing to form a planar vortex flap which acts as a pressure shield. The present improvement extends the pressure generating forward concave wing undersurface of this system into an upward reflexed aft surface so as to benefit from the increased pressure provided by the downstream upwash vortex field. This allows the aft portion of the wing to serve as the energy recovery section by achieving the pressure required for lift on the undersurface of this aft wing portion at a lesser angle with reduced drag. This stream-wise series of functions specifies the wing undersurface as concave, convex, and concave sequentially in the flow direction, thus corresponding to the upper element of a planar supersonic nozzle.

Abstract: A supercritical wing section having a large average leading edge radius of curvature, followed on the upper surface by a reduction in curvature and then a knee, or region of positively increased curvature, at between 3% and 13%, preferably 5% to 10%, chord the region of increased curvature being followed by a region of low curvature extending for 30% to 90% of the chord, whereby in use of the wing at low speeds the peak velocity and peak suction are contained, in use thereof at intermediate speeds local supersonic expansion is minimized, and in use thereof in supercritical conditions a region of high expansion, stabilized over the region of increased curvature, is created.

Abstract: A supercritical aerofoil having a large leading edge radius of curvature, a radius of curvature over substantially the whole upper surface appreciably higher than the mean radius over the front half of the lower surface, a concave surface to the rear half of the lower surface, and a thickness/chord ratio of 10- 14%.

Abstract: A thin, high performance swept wing of the tapered type with an improved leading edge characterized by (1) camber that increases from a minimum near the wing root to a maximum near the wing tip, and (2) substantially a constant leading edge radius extending substantially across the wing span which defines a "blunt" contour. The wing in combination with a T-tail aircraft with a stick shaker/pusher activated by a rate of change of angle of attack sensor and optionally a strake between the leading edge and a wing tip tank which intrinsically combine to define a system that enhances aircraft performance by reducing minimum airspeed without impairing aircraft performance at high subsonic Mach (M) numbers.

Abstract: An airfoil having an upper surface shaped to control flow accelerations and pressure distribution over the upper surface and to prevent separation of the boundary layer due to shock wave formulation at high subsonic speeds well above the critical Mach number. A highly cambered trailing edge section improves overall airfoil lifting efficiency.

Abstract: An object disposed in a fluid flow and defined by two surfaces, each extending along a stream line and one of said two surfaces having a reference contour. To eliminate the danger that a violent oscillation is generated due to resonance between the natural oscillation of the object and the oscillation caused by Karman's vortex which develops at the downstream end portion of the object, said downstream end portion of the object is so formed as to provide a configuration satisfying the following relations:R1/TV.ltoreq.0.2 and R2/TV=6-10where, R1 is a radius of curvature of the first portion of object's downstream end portion which is continuous with said reference surface, R2 is a radius of curvature of the second portion of object's downstream end portion extending between said first portion and the other surface, and TV is the minimum thickness of the object between said two surfaces measured from the joining point or juncture between said second portion and the other surface.

Abstract: An aircraft having a wing provided with a semicircular recess in its trailing edge. A powered rotor rotatable about the axis of the recess and having blades whose tips extend close to the semicircular edge below the upper surface of the wing. The rotor produces direct upward thrust on the aircraft and also creates low pressure over the wing and higher pressure below the wing to augment the direct upward thrust of the rotor. Centrifugally moving air impinges on the edge surface of the recess to produce forward thrust. .Iadd.