Abstract: An aircraft includes a wing having a positive dihedral, the wing having a tip and a wing tip device mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region inclined at a cant of more than 180 degrees. The region is arranged to generate lift during flight. The region inclined at a cant of more than 180 degrees may be located at the distal end of the wing tip device. The wing tip may be swept and may aeroelastically deform during flight.

Abstract: A winglet for an aircraft wing is provided. The winglet has an airflow control arrangement, for example in the form of a trailing edge flap (20) by means of which lift generated by the winglet can be varied. The control arrangement desirably forms part of a manoeuvre load alleviation system (22) for the aircraft.

Abstract: A tip device to act as an outboard continuation of an aircraft wing or other aerodynamic lifting surface has a downward cant angle, a leading edge swept back in relation to the leading edge of the inboard lifting surface, and a chord reducing in the outboard direction of the device. A favourable balance between induced drag reduction and increased wing root bending moment can thereby be achieved. Preferably the device also has an upwardly canted portion at its root end so that the downward cant commences from a relatively elevated spanwise location, thereby alleviating any ground clearance problems.

Abstract: An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing, and an angled portion that projects at an upward angle from the body portion. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and increase efficiency.

Abstract: An improved supersonic laminar flow wing structure, on a supersonic aircraft, having one or more of the following: a strake extending forwardly of the wing inboard extent, a raked wing tip, a reversed fillet at the strake or fuselage junction, an inboard leading edge flap extending over less than about 15% of the inboard wing panel span, and a hybrid plain-split flap having a lower surface portion deflectable downwardly relative to plain flap extent.

Abstract: A wind spoiler including a vertical member mounted vertically along a roof of a structure to extend above the plane of the roof for creating turbulence in wind flowing over the roof.

Abstract: Tip feathers, including forward swept tip feathers, and associated aircraft systems and methods are disclosed. A system in accordance with one embodiment includes an aircraft wing having an inboard portion, an outboard portion, and a leading edge having an aft wing sweep angle at the outboard portion. A first feather is fixed relative to, and projects outwardly from, the outboard portion of the wing and has a leading edge with a first, forward sweep angle relative to a pitch axis of the wing. A second feather is fixed relative to, and projects outwardly from, the outboard portion of the wing at least partially aft of the first feather, and has a leading edge with a second, aft sweep angle relative to the pitch axis.

Abstract: An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing, and an angled portion that projects at an upward angle from the body portion. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and increase efficiency.

Abstract: A winglet and methods of operating an aircraft using the winglet. In some embodiments, the winglet can be mounted to the wingtip of an aircraft and has three segments or portions, namely, a mounting portion, an upwardly extending portion, and a reverse portion, or a portion that extends in an inboard direction.

Abstract: A multi-segment flap fence is incorporated into the wing such that a lower fence structure is attached to the underside of the fixed wing, an upper fence structure is attached to the main flap (e.g., at the outboard end). The two flap segments are configured to slideably articulate with respect to each other when the flap is extended to form a composite flap fence having an area that is substantially equal to the sum of the surface areas of the upper and lower flap fence structures. In one embodiment, the area of the upper fence is less than that of the lower fence.

Abstract: The invention relates to a wingtip extension comprising a leading edge and a trailing edge, which wingtip extension is affixable to an outer end of a wing, wherein the leading edge, at least in some sections, is essentially straight, and the straight section of the leading edge comprises a leading-edge sweep angle that exceeds the leading-edge sweep angle of the wing, and the local depth of the wingtip extension gradually decreases between a connecting region for connection to the wing and the outer end of the wingtip extension. By means of a wingtip extension according to the invention, in a delta wing a vortex burst region is positioned just behind the wingtip, as a result of which vortex burst region the cores of wingtip vortices burst and eventually become unstable, so that as a result of this the wake vortices of the aircraft can be reduced. The invention furthermore relates to a wing, comprising wingtip extensions according to the invention, as well as to an aircraft comprising such a wing.

Abstract: A wing incorporating a wing tip with a curved leading edge and a curved trailing edge to minimize induced drag for a given wing form is disclosed. The curve of the leading and trailing edges of the wing tip may be described generally as parabolic, elliptic, or super elliptic. A finite tip segment may be included with a sweep angle between the end of the curved leading edge and the end of the curved trailing edge. The wing tip may also include a spanwise camber.

Abstract: A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence during landing and/or other operating conditions, and stow the flap edge fence during other operational conditions such as cruise. The flap edge fence is controlled passively by ambient temperature or actively by a controller based on temperature changes corresponding to various operating conditions.

Abstract: Systems and methods for providing variable geometry winglets to an aircraft are disclosed. In one embodiment, a winglet includes a base portion configured to attach to a wing. The winglet further includes a body portion. In turn, the body portion includes at least one of a deflectable control surface, a shape memory alloy (SMA) bending plate, and a SMA torque tube. The base portion is configured to attach to the wing such that the body portion projects at an upward angle from the wing.

Abstract: A winglet comprising a root connected to a distal end of a wing; an upwardly angled section; a tip; and a transition between the upwardly angled section and the tip at which an outboard cant angle of the winglet decreases relative to a reference plane of the wing. In one embodiment the winglet is continuously curved and includes a point of inflection at which the span-wise curvature of the winglet changes sign. In another embodiment the upwardly angled section is planar. The winglet generates a tip vortex when in flight. The tip vortex is displaced outboard from the winglet due to the decrease in outboard cant angle at the transition.

Abstract: A transferable modified leading edge for a wing is detachably mountable to a parent wing. The parent wing may use a NACA 23000-series airfoil. A modified wing tip may be used in conjunction with the modified leading edge. The modified leading edge can be mounted to a parent wing in a way that does not damage the parent wing. The modified leading edge and wing tip can provide increased lift.

Abstract: A wing for of aircraft has a wing tip shape that has a profile that extends in the direction of the span of the wing, and across the direction of the span of the wing extends from the wing leading edge to the wing trailing edge. The profile is delimited by a first skin and a second skin, with a winglet, arranged on the wing end. The winglet is substantially planar, and has a transition region arranged between the wing and the winglet, that extends from a connection on the wing to a connection on the winglet. The curvature of the local dihedral can increase in the transition region from a low level or a level of zero at or near the wing intersection in the outboard direction.

Abstract: A capped winglet comprising a helical portion having a smooth vertical curvature of 180°±approximately 20° from the plane of the unbounded end of a wing, and a generally planar cap contiguous with the helical portion of the winglet at the end of its curvature away from the wing, the cap having a free inboard end and a chord tapered toward the free end.

Abstract: An aircraft can include a wing with a leading edge and a trailing edge. The wing has a main body and movable control surfaces coupled to the main body. The wing generates lifting forces when the aircraft is in flight. The movable control surfaces can be used to control the generated lifting forces. A spanwise flow inhibitor extends from the outer wingtip of the wing. At least one gurney flap extends generally downwardly from at least a portion of the trailing edge of the wing. The flap at least partially counteracts a change in center of lift attributable to the spanwise flow inhibitor.

Abstract: An aircraft has a fuselage and a pair of wings joined to the fuselage at a dihedral angle. A wing extension, such as an angled winglet or a wing-tip pod, is joined to a distal end of each of the wings. A top-surface antenna lies in each of the top surfaces, and a bottom-surface antenna lies in each of the bottom surfaces. The antennas are preferably flat-panel antennas such as phased-array antennas.

Abstract: Winglets with recessed surfaces, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a wing having an inboard portion and an outboard portion, and further includes a winglet coupled to the wing at the outboard portion. The winglet can have a first surface facing at least partially inboard and a second surface facing at least partially outboard, with the first surface including a recessed region.

Abstract: Reduced span wings with wing tip devices, and associated systems and methods are disclosed. A method for designing a wing in accordance with a particular embodiment includes establishing a target lift value for a winglet to be attached to a wing, the wing having a wing root, a wing tip and a twist distribution that results in a loading at the wing tip that is higher than a target loading level. The method can further include selecting a planform shape of the winglet to produce less of an increase in loading at the wing tip compared to the wing tip loading produced by other winglet planform shapes having the same target lift value. Accordingly, in particular embodiments, the winglet design can offset or at least partially offset the reduced wing tip loading produced by the twist distribution.

Abstract: Improved supersonic laminar flow wing structure, on a supersonic aircraft, having one or more of the following: strake extending forwardly of the wing inboard extent, raked wing tip, reversed fillet at strake or fuselage junction, inboard leading edge flap extending over less than about 15% of the inboard wing panel span, hybrid plain-split flap having a lower surface portion deflectable downwardly relative to plain flap extent.

Abstract: An aircraft (10), in particular a trainer aircraft with improved aerodynamic performance, having a configuration able to keep a directional stability and a very good aerodynamic behaviour even at very high angles of attack, where, traditional configurations prove themselves inefficient. In particular, this configuration foresees a forebody (52) with variable section, optimised for high angle of attack flights, a LEX vortex control device (72) at least one diverterless air intake (46), and a wing profile (18, 20) optimised in order to reduce the buffet effects typical of low aspect ratio wings with thin profile and variable camber. The aircraft (10) presents, finally, staggered tails (44 and 38), to optimise the aerodynamic performance.

Abstract: Wingtip feathers, including paired, fixed features, and associated systems and methods are disclosed. A method for designing an aircraft wing in accordance with a particular embodiment includes providing a geometry for a wing having an upper surface, a lower surface, and an aft-swept wing leading edge. The method can further include selecting a geometry and location for a first feather and a second feather, based at least in part on a predicted effect of the feathers on a location of a shock at the upper surface of the wing at transonic flight conditions, with the first feather being positioned at an outboard tip of the wing and the second feather being positioned at the outboard tip of the wing aft of the first feather.

Abstract: Methods for increasing the performance of a foil (100) by using tip droop (102) having an inward directed camber capable of generating an inward directed lifting force on the tip droop (102) in order to control spanwise flow conditions adjacent the tip (112) of a foil (100). Methods for varying the inward lifting shape of a tip droop (102) are provided along with methods for varying the angle of attack and camber of the tip droop (102) as the angle of attack of the foil (100) is changed and as spanwise flow conditions vary.

Abstract: Tip feathers, including forward swept tip feathers, and associated aircraft systems and methods are disclosed. A system in accordance with one embodiment includes an aircraft wing having an inboard portion, an outboard portion, and a leading edge having an aft wing sweep angle at the outboard portion. A first feather is fixed relative to, and projects outwardly from, the outboard portion of the wing and has a leading edge with a first, forward sweep angle relative to a pitch axis of the wing. A second feather is fixed relative to, and projects outwardly from, the outboard portion of the wing at least partially aft of the first feather, and has a leading edge with a second, aft sweep angle relative to the pitch axis.

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 wing for use on a supersonic aircraft that includes an inboard section a central section of the wing outboard of the inboard portion, and an outboard section. The outboard section can be a winglet oriented anhedrally relative to a lateral axis of the supersonic aircraft. Leading edge segments on the inboard section, central section and outboard winglet may have mounted thereon leading-edge flaps. These flaps are adjusted by a control system operable to reposition the leading-edge flaps in order to improve the aerodynamic performance of the supersonic aircraft. This winglet promotes sonic boom minimization. Further, the wing tip anhedral allows greater inboard dihedral. This effectively pushes lift aft for sonic boom and control purposes while minimizing the movement of control surfaces.

Abstract: Systems and methods for providing variable geometry winglets to an aircraft are disclosed. In one embodiment, a winglet includes a base portion configured to attach to a wing. The winglet further includes a body portion. In turn, the body portion includes at least one of a deflectable control surface, a shape memory alloy (SMA) bending plate, and a SMA torque tube. The base portion is configured to attach to the wing such that the body portion projects at an upward angle from the wing.

Abstract: An aircraft comprises a wing having a positive dihedral, the wing comprising a tip and a wing tip device mounted in the region of the tip. The wing tip device is generally downwardly extending and has a region inclined at a cant of more than 180 degrees. The region is arranged to generate lift during flight. The region inclined at a cant of more than 180 degrees may be located at the distal end of the wing tip device. The wing tip may be swept and may aeroelastically deform during flight.

Abstract: The present invention relates to a device for adapting aerodynamic characteristics of a wing element (1), wherein the device comprises a winglet (2), wherein the winglet (2) is movably attachable to the wing element (1), and wherein the winglet (2) or parts of the winglet is or are rotatable in relation to the wing element (1) such that an associated rotary axis (7) with a main direction of extension (6) of the wing element (1) encompasses an angle that differs from 90°.

Abstract: A system and a method according to the invention reduce wake turbulence of an aircraft in that a component affixed to the extremity of the wing of an aircraft disturbs the rolling action of the air in the region of the outer wing by periodic hingeing movements.

Abstract: The present development relates to an improved wing having a tip tank assembly. The tip tank assembly is attached to a distal end of an outer wing section. The tip tank assembly includes a tank, a pair of mounting brackets and a fairing assembly. The fairing assembly includes a nose piece, a central piece, a tail piece, an inner end plate, and an upper close out piece. The inner end plate extends perpendicularly downward from a lower surface of the outer wing section eventually terminating at a bottom portion of the central piece. The inner end plate acts as an air dam to trap high pressure air that is generated during flight, substantially increasing the lift of the wing. Lastly, the upper close out piece extends between an upper wing surface and an upper portion of the central piece increasing the overall wingspan of the aircraft.

Abstract: To control and particularly steepen the landing glide path of an aircraft, a respective aerodynamic component mounted on each wingtip includes a fixed plane member and a pivotable control element pivotally connected to the fixed plane member. The pivot axis is perpendicular to the major plane of the wing. The pivotable control element can be selectively pivotally deflected about the pivot axis relative to the fixed plane member, so as to thereby increase the overall drag without influencing the overall lift of the aircraft. This achieves a fine adjustment that is superimposed on the basic landing configuration established by the setting of the flaps, spoilers, engine thrust, etc. By increasing the drag without influencing the lift, this steepens the landing glide path slope.

Abstract: Methods for increasing the performance of a foil (100) by using tip droop (102) having an inward directed camber capable of generating an inward directed lifting force on the tip droop (102) in order to control spanwise flow conditions adjacent the tip (112) of a foil (100). Methods for varying the inward lifting shape of a tip droop (102) are provided along with methods for varying the angle of attack and camber of the tip droop (102) as the angle of attack of the foil (100) is changed and as spanwise flow conditions vary.

Abstract: A lifting foil for an aircraft, a hydrofoil or the like having a pair of courses or wings. Vortex losses due to spanwise fluid flow are substantially reduced by joining the tips of the courses with flow guides configured for jointly terminating the undesired flows. Termination is effected by providing the flow guides with crossections cambered for reducing the dynamic pressure of fluid flowing in a spanwise direction across flow guide surfaces.