Flügelspitzenvorrichtung und verfahren

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[0001] wing final device The present invention relates to a for attachment to the outboard end of an airfoil. Also with the wing wing final device , an aircraft with the tail planes, a process of installing or retrofitting the wing final device on a wing, a method for modifying an existing wing final devicewing final device and a method for operating of an airfoil with the.

[0002] A wing final device be charged on the outboard end of an airfoil mounted, so as to reduce the induced resistance to the aerofoil. For example, this may result in improved fuel efficiency and in the case of a lead airplane wing reduced carbon emissions.

[0003] a plurality of forms can wing final devices.

[0004] A winglet wing-like element is a, which extends from the extending from wing end. A winglet may extend upwardly or downwardly from the NASA TN D -8260 wing end from ., entitled "A Design Approach and Selected [...][...] at high [...]speeds for Wing-Tip Mounted winglet (A construction beginning and selected wind tunnel-Results subsonic speeds for wing-finalinstalled winglet at high)", Whitcomb, R. T., 1976, describes a wing final device , the a lower winglet (wing end extending downwardly from the) from an upper (wing end from extending upwardly from the) has winglet. In NASA TM 81230 calculating such terminals is entitled the "effect of winglet or the [...] Drag of Ideal Wing Shapes (action of winglet or the induced resistance of ideal wing forms)", Jones and [...][...][...] , 1980, recommended.

[0005] A wing final devicewing end plate is a special form of a, the vertically extends both above and below the wing end. US 4, 714, 215 describes a wing final fence.

[0006] Another example wing final extensionwing final device is a an uneven, i.e., it extends out of the plane of the aerofoil, to which it is secured. A winglet can be regarded as a special example an uneven wing final extensionwing final extension. US 2002/0162917 describes an uneven, having a continuously increasing curvature of the local dihedral, a continuously increasing sweepback (both on the [...] also at the trailing edge) and a continuously decreasing outboard direction has in the chord.

[0007] A winglet can include a substantially planar portion is connected by a curved transition region with the wing end , so as to form an integrated winglet, such as, for example, in US 5, 348, 253 described. Transition area has a constant radius of curvature on. It is to say that the specified integration overlapping resistance effectswing end reduced at the.

[0008] Alternatively, include a substantially planar portion a winglet is connected with the by a uneven wing endwing end -extension region, such as described in WO 2008/061739. The continuously increasing curvature of the local dihedral wing end -extension region has a uneven in the outboard direction on. It is to say that the wing end extension range , compared with an integrated winglet with a transition of constant radius, on the overlapping resistance effectswing end further reduced.

[0009] a substantially planar wing final extensionwing final device is a Another example, such as in US 6, 089, 502 described beveled wing end , extends out of the plane of the wing which is substantially not. Beveled resistance reduction decreasewing ends can achieve a similar as winglet.

[0010] restrictions of span for aircraft, e.g. due to [...] - [...] - gate borders or airplane category -drawing, mean, the winglet or uneven wing final extensions , rather than chamfered wing ends , need to be applied, so as to reduce the induced resistance to the aerofoil. Since winglet out of the plane of the aerofoil (and general uneven wing final extensions), to which they are attached, extend, can be achieved an effective increase in actual (what the vortex resistor reduces the aerofoil) wing aspect ratio , without significantly to increase the wing-span.

[0011] The problem is conventionally restrictions of spanwing span of the aircraft by the optimizing the in from said base mold (full fuel load), when the apply restrictions of span , dissolved. However, , aeroelastic effects during flight due to the induced bending on the wing form of, the wings-span the resulting flight form usually reduced and is therefore no longer be optimal. This problem is even more significant with a greater use of relatively flexible wings, to reduce the structural weight, the, compared with stiffer constructions, tends, to lead to an increased wing buckling under aerodynamic load.

[0012] A first aspect of the invention provides a ready at the outboard end of an airfoil mount wing final device , wherein the wings have a defined plane of the flap, wherein the comprises wing final device : an upper wing-like element, with respect to the plane of the flap projecting upward and has a trailing edge, and a lower wing-like element is fixed with respect to the upper wing-like element and a root-chord and has a trailing edge, wherein the root-chord of the lower wing-like element intersects with the upper wing-like element and the lower wing-like element projecting downwardly from the interface, wherein the upper wing-like member is greater than the lower wing-like element and the rear edge of the lower wing-like element at the interface adjacent to the trailing edge of the upper wing-like element and wherein an included angle between the upper and lower wing-like element at the interface is less than or equal to 160 degrees.

[0013] A second aspect of the invention provides a ready Aerofoil, wing final device according to the first aspect of the invention the an outboard end and a fixed at its outboard end, has.

[0014] A third aspect of the invention provides an aircraft ready, after the second aspect has the wing.

[0015] A fourth aspect of the invention provides a method of installing or retrofitting a ready wing final device on a wing, the method comprising securing a wing final device after the first aspect at the outboard end of the aerofoil comprises.

[0016] A fifth aspect of the invention provides a method for modifying a wing final device ready is fixed or can be fixed at the outboard end of an airfoil, wherein the wings have a defined plane of the flap, wherein the existing wing final devicewing-like element comprises an upper, projecting upward with respect to the plane of the flap and has a trailing edge, and the method includes providing a lower wing-like element is smaller than the upper wing-like element and has a trailing edge and a root profile chord line , and fixing the lower wing-like element comprises at the upper wing-like element in such a way that: the root-chord of the lower wing-like element intersects with the upper wing-like element projecting downwardly from the interface and the lower wing-like element, and in that the trailing edge of the lower wing-like element at the interface adjacent to the trailing edge of the upper wing-like element and that an included angle between the upper and lower wing-like element at the interface is less than or equal to 160 degrees.

[0017] A sixth aspect of the invention provides a method for operating a wing ready, the has a wing final device , at the outboard end is attached to the wing, wherein the wings have a defined plane of the flap and the wing final device comprises: an upper wing-like element, with respect to the plane of the flap projecting upward and has a trailing edge, and a lower wing-like element is fixed with respect to the upper wing-like element and a root-chord and has a trailing edge, wherein the root-chord of the lower wing-like element intersects with the upper wing-like element and the lower wing-like element projecting downwardly from the interface, wherein the upper wing-like member is greater than the lower wing-like element and the rear edge of the lower wing-like element at the interface adjacent to the trailing edge of the upper wing-like element and wherein an included angle between the upper and lower wing-like element at the interface is less than or equal to 160 degrees, and wherein the method includes exposing the wing aerodynamic loads comprises such that the deformation into a state enters into a wing formaeroelastic , wing bucklingwing rootwing final device about the rotation of the in the caused in such a way that the end of the lower wing-like element in the spanwise direction further than the end of the upper wing-like element extends overboard.

[0018] The invention is advantageous therein that the lower wing-like element acts, at least some of the reduction in the wing-span that it, on reason flight formaeroelastic deformation in the occurs, compensates for, while the upper and lower wing-like element may be further improved, to satisfy any valid restrictions of span in the base mold.

[0019] It is been shown that the addition of the lower member to a wing final device , the only (e.g. a winglet) comprises an upper wing-like element, the resistance at the combination of aerofoil and 1.9% reduced overall by another $ wing final device , with a further round eddy resistance decrease of 25 to 40% with respect to the afforded by the lower element alone.

[0020] The approximate conformity of the trailing edges of said upper and lower members is important, so as to avoid eddy dragging turbulence effects. The trailing edges must not directly coincide, but must adjoin one another, so as to avoid that the encounters of said one member at the interface acts to the flow over the other element.

[0021] The included angle between the upper and lower wing-like element at the interface is important in such a way that provides an increase in the span flight form the lower element in the. The inclination angle of the lower element (i.e., the angle between the vertical and the element x-z-plane) can be optimized, to achieve the maximum flight formspan increase in the, with due regard to the minimizing of overlapping effects at the interface. It must be remembered that a [...] an included angle between vertical upper and lower elements of about 180 degrees and the lower element provides a negligible increase in actual span flight form so in the.

[0022] The upper wing-like member is greater than the lower wing-like element. The element sketch surface of less than about 25% of the lower wing-like element can a plan area of the upper wing-like element. It must be remembered that the plan area of each element is viewed in a plane, from that of the different wing plan surface. The plan area of the lower element can be designed that it provides the required [...] , during the cruise flight- friction resistance disadvantage is minimized, and ensures a good high lifting efficiency at low speed. restrictions of ground can limit the size of the lower element for the height distance.

[0023] The lower wing-like element is immovably with respect to the upper wing-like element. The wing final device is immovably with respect to the wing. The invention relates to non-mobile wing final devices , since these generally heavier than fixed devices, what a Performance Benefit can compensate for. Moreover, the solve the problem of somewhat trivial wing final devicesrestrictions of span with movable.

[0024] A included angle between the chord plane and the lower wing-like element 110 degrees can at least. The lower member extends from the outboard end of the aerofoil of overboard therefore, and can and lower members between the Aerofoil-underside overlapping effects are minimized.

[0025] The included angle at the interface between the upper and lower wing-like element 80 degrees and 90 degrees can at least preferably equals at least. This helps, overlapping effects between said upper and lower members to minimize at the interface.

[0026] The lower wing-like element can be substantially planar.

[0027] Alternatively, the lower wing-like element substantially be uneven. In particular, the lower element a [...] , e.g. a negative twist, have. The span curvature with increasingly negative V-shape can lower member a from the root towards the end.

[0028] The lower member may have a lateral direction relative to the vertical x-z-plane a toe angle.

[0029] The lower member can have a positive sweep angle.

[0030] Specifically can have a positively swept leading edge the lower member. The positive sweep angle of the leading edge of the lower element may be similar to that of the upper element.

[0031] The upper wing-like element can a substantially planar part contain.

[0032] The upper wing-like element can be substantially planar. The upper member a winglet can be.

[0033] In another embodiment, a substantially planar portion and the upper wing-like element can an arcuate transition region, which is suitable, the outboard end of the aerofoil uniformly in the substantially planar portion of the upper wing-like element to pass, contain. The upper wing-like element can be an integrated winglet. Transition area can have a constant radius of curvature. The course helps, to reduce wing endoverlapping resistance effects at the.

[0034] In yet another embodiment a substantially planar portion and the upper wing-like element can an uneven curved wing final extension , which is suitable, the outboard end of the aerofoil uniformly in the substantially planar portion of the upper wing-like element to pass, contain. The upper wing-like element can be a winglet, by an uneven wing final extension extends into the wing. The uneven wing final extensionoutboard direction have an increasing curvature of the local dihedral in the can. The wing final extension helps, overlapping resistance effects , compared with an integrated [...] "

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Winglet with a transition of constant radius, to reduce further.

[0035] The upper wing-like element can be a substantially uneven curved wing final extension. A continuously increasing curvature of the local dihedral can The extension, a continuously increasing sweepback (both on the [...] also at the trailing edge) and a continuously decreasing outboard direction have in the chord.

[0036] The upper wing-like element can a [...] , e.g. a negative twist, from the root towards the end.

[0037] The upper wing-like element can have a toe angle with respect to the vertical x-z-plane.

[0038] The upper wing-like element can have a positive sweep angle. Specifically a positively swept leading edge can have the upper member. The positive sweep angle of the leading edge of the upper member can be similar to that of the lower element.

[0039] The interface between the lower wing-like element and the top wing-like element are located at the outboard end of the aerofoil can.

[0040] Alternatively, the interface between the lower wing-like element and the top wing-like element are located outboard of said outboard end of the aerofoil. This can be particularly favourable, when the upper member is uniformly into the outboard end of the aerofoil must also strive to make. In this case, the interface are located on the lower surface of the upper element.

[0041] The root-chord of the lower element along only a portion of the local chord can located at the interface of the upper element extend.

[0042] If said airplane is on the ground and is exposed to full fuel load a deflection downwards as a result of the tail planes, the end of the lower wing-like element not further in the spanwise direction than the end of the upper wing-like element extend overboard. This allows, for example, the ends of each of said upper and lower member are located at an airport- gate border.

[0043] If said airplane is on the ground and is exposed to full fuel load a deflection downwards as a result of the tail planes, can the span extending of the end of the lower wing-like member is substantially equal to the the end of the upper wing-like element be span extending. Alternatively, the wing-like element exceed the span extendingspan extending of the end of the lower wing-like element to the end of the upper, end of the upper member is substantially less than when the span of the the airport- gate border.

[0044] If the aircraft is in flight, as a result the end of the lower wing-like element in the spanwise direction can aeroelasticwing form further than the end of the upper wing-like deformation of the element extend overboard.

[0045] embodiments of the invention will now described, with reference to the attached drawings, in which:

[0046] Figure 1 an aircraft-Aerofoil of the state of the art with an upper winglet illustrates, shown a) in its base mold and b) in its flight form ,

[0047] Figure 1 illustrates the detail A of Figure 2, at the bottom and as a result of the loss of the span borderwing deformation under aerodynamic load shows span,

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[0048] Figure 3 a illustrates a first embodiment of a aircraft-Wing/ wing final device , comprising a planar top winglet and a planar lower winglet, shown a) in its base mold and b) in its flight form , and from said lower element flight form recovered span illustrates in the,

[0049] Figure 4 the aircraft-Wing/ wing final device according to the first embodiment, illustrating in detail the,

[0050] Figure 5 and 6graphisch the further reduction in the resistance as a result of the lower element at first embodiment illustrate,

[0051] Figure 7 a (in the bottom mould) according a wing final device Airplane-Wing/illustrates a second embodiment, comprising a planar top winglet and an uneven lower winglet,

[0052] Figure 8 (in the bottom mould) an aircraft-Wing/ wing final device after a third embodiment illustrates a, comprising an integrated upper winglet and a planar lower winglet,

[0053] Figure 9 a (in the bottom mould) a Airplane-Wing/ wing final device after a fourth embodiment illustrates, comprising an upper winglet, the let is run with an uneven wing final extension in the wing, and a planar lower winglet (although can be also employed an uneven lower winglet), and

[0054] Figure 10 illustrates a perspective view of the fourth embodiment the wing final deviceairplane wing /the,

[0055] Figure 11 shows a top view of the aircraft wing wing final device the fourth embodiment illustrates the /,

[0056] Figure 12 after a fifth embodiment illustrates an aircraft-Wing/a wing final device , comprising an uneven wing final extension (upper) and a planar lower winglet, and

[0057] Figure 13 illustrates a perspective view of the fifth embodiment, the wing final deviceairplane wing /the.

[0058] Figure 1 illustrates an aircraft-Aerofoil 1 of the prior art, a indoor airborne wing root 2 and 3 comprises a outboard wing end. A wing final device , the 4 comprises an upwardly extending winglet, be charged on the 1st 1 1 in Figure 3 of the aerofoil is outer on-board end in a The Aerofoil) its base mold (i.e., with the aircraft is on the ground and with a full fuel load in the wing) and b) (i.e., with deformation due to aerodynamic loading) its flight form shown.

[0059] Figure 2 illustrates the detail A of Figure 1, and the broken line 5 illustrates a restriction of span , the the aircraft, e.g. due to airfield compatibility - gate borders or airplane category -drawing, are imposed. The span border in Figure 5 applies to the 2a) shown base mold. Figure 2b) illustrates the loss due to 6 at Aerofoil-span flight formwing deformation in the. This loss can be up to 3% 6 wherein the span.

[0060] Figure 3 illustrates an aircraft-Aerofoil 101 according to a first embodiment, comprising a planar top winglet 104 107 104 and a planar lower winglet is at the outboard end 103 of the aerofoil. The upper winglet 101 fixed. The 104 108 101 defines a plane of the flap projects. The upper wing with respect to the plane of the flap 108 upwardly winglet. 109 and a root 110 104 has a winglet The upper end on. 111 and 112 on a root end has a winglet The lower. The 104 112 of the lower chord intersects with the upper winglet winglet, and the lower downwardly from this interface 107 jumps from winglet before. The upper and lower winglet 104, 107 have in each case a leading edge and a trailing edge, and the trailing edges border each other at the interface. Figure 3a) illustrates the aircraft-Aerofoil in its base mold 101, 104 and the end 109 of the upper 111 wherein the end 107 on the winglet span border 105 coincide the lower winglet. Figure 3b) illustrates the 101 in its deformed airplane wingflight form and shows, as a result of the potential loss in the span 104 106 113 by an increase in the span upper winglet, recovered from the lower winglet 107 is reduced. 107 113 This increase is about 2% at the span on the basis of the lower winglet.

[0061] Figure 4 illustrates the aircraft-Aerofoil 101 of the first embodiment in greater detail. The lower 107 is sized and aligned winglet, span increaseflight form is maximized in the that the, while 107 overlapping effects at the interface between the lower and the upper winglet 104 are minimized winglet. ground spacer height G between the base and the tip is also a 107 111 of the lower winglet taken into account. The resulting geometry ensured wing element an included angle between the upper and lower of around 108 132° and an included angle between the chord plane 107 of around 128° and the lower winglet. The 107 has a winglet-plan area of around 20% lower winglet the plan area of the upper 104 on winglet. The relatively small size of the lower winglet friction resistance disadvantage during the journey the minimized 107, during the required optimum [...] is supplied.

[0062] Figure 5 and 6 illustrate graphically the effect of the addition of the lower [...][...]eddy resistance characteristics 107 on the 5 and 6, the line 101 of the aerofoil with circular markings. In Figure reference wing constitute a, 101 corresponds to the the aerofoil, with one end close to an imposed wing final devicespan border without any. The line 101 with only the upper 104 [...]cross markings illustrates the tail planes with (dimensioned, as in NASA T 81230, entitled "effect of winglet on the [...] Drag of Ideal Wing Shapes (effect of winglet on the induced resistance of ideal wing forms)", Jones and [...][...][...] , 1980, recommended), and the line with the triangular marks represents the Aerofoil [...] 104 101 with each of the upper and lower, 107 constitute. Figure 5 illustrates the relationship between the (CL, CD) and shows [...] the resistance coefficient for improvements in the ratio of buoyancy to resistor for the wing 104 101 with each of the upper and lower [...] , 107, compared with only one upper reference wing and the aerofoil with both the [...]. Figure 6 illustrates a resistance saving[...] 107 of around 1.9% on the basis of adding of the lower (CL = 0.5) in relation to the wing in which at a mean buoyancy coefficienttravel weight with only the upper element 107 104 [...]eddy resistance decrease is ensured by the lower. The a further reduction of around 25 to 40%.

[0063] Figure 7 illustrates an aircraft-Aerofoil 201 according to a second embodiment, comprising a planar top 207 201 204 and an uneven lower winglet. The Aerofoil winglet defines a leaf plane 208, 208 204 projects with respect to the plane of the flap and the upper winglet upwardly. 201 203 204 is mounted at the outboard end of the aerofoil The upper winglet. The 207 has a root-chord 212 on lower winglet, 204 intersects with the upper winglet. The lower winglet projects downwardly from the interface 207. 209 210 204 having one end and a root The upper winglet on. The 211 207 has a end on lower winglet, 209 205 in the spanwise direction to the coincident with the end span border. The upper and lower winglet 204, 207 have each having a leading edge and a trailing edge, and the trailing edges border each other at the interface. The 201 is shown in Figure 7 in its base mold wing, wherein the is enforced span border 105.

[0064] The 207 has an increasing curvature of the local dihedral lower winglet 212 211 on the end from the root. The [...]toe-out angle 207 can have a lower winglet, to optimize the [...] the wing final device.

[0065] The wing final device 201 is been optimized for the wing, so that the under aerodynamic span increaseflight loads is maximized, while the between the lower and the lower surface of the aerofoil overlapping effects 201 and 207 winglet between the lower and the upper winglet 204, 207 are minimized. The resulting optimized geometry has an included angle between the upper and lower winglet 204, 207 and 208 from around 120° and an included angle between the chord plane 207 from around 138° on the lower winglet. In the flight form 207 a further gain in the span the lower winglet guaranteed, compared with the lower winglet 101 107 of the aerofoil, in principle due to the increased 211 207 212 for fleas of the lower and the flexibility from the root end winglet the lower winglet 207, under flight loads straighten.

[0066] Figure 8 illustrates an aircraft-Aerofoil 301 according to a third embodiment, comprising an integrated upper 301 307 304 and a planar lower winglet. The Aerofoil winglet faces 303 on an outboard end is fixed to the the integrated upper winglet 304. 309 310 304 having one end and a root The upper winglet on. 310 303 304 is at the outboard end by its root end winglet The upper 301 fixed of the aerofoil. The 314 304 has a substantially planar portion and a upper winglet 315 on curved transition area. Transition area 315 is suitable, the outboard end 314 301 303 of the aerofoil to pass evenly in the substantially planar portion. The 315 has a substantially constant radius of curvature R on curved transitional area.

[0067] The 315 307 on the lower surface of the transition region is lower winglet 304 attached winglet of the upper. 311 and 312 on a root end has a winglet The lower. The root-chord of the lower with the upper 304 307 intersects winglet winglet, projects downwardly from the interface and the lower winglet. The upper and lower winglet 304, 307 on each have a leading edge and a trailing edge, and the trailing edges border each other at the interface.

[0068] Transition area helps 315, 314 301 overlapping effects between the substantially flat portion to reduce and the wing.

[0069] 305 309 304 intones the span border The End substantially the upper winglet in the vertical line 307 to the end 311 of the lower winglet x- [...]. A included angle between the upper and lower winglet 304, 307 is approximately 84°. It is preferable that this angle is at least 80 °, overlapping effects between the upper and lower so as winglet 304, 307 to avoid. As the interface 315 is located on the lower surface of the integrated transition region is the angle between the tangent of the lower and the lower winglet transient area surface 307 measured. A included angle between the plane of the flap 307 is approximately 125° 308 and the lower winglet. The 304 has a substantially flat portion 314 of the upper direction relative to the vertical angle of inclination in the winglet x-z-plane 7a 15° on from around.

[0070] The[...]element sketch surface of about 25% of the plan area of the 307 has a lower [...] 304 on top. During 307 is substantially flat the upper winglet, it may have a certain [...] from the root to the end 311 312. The [...]toe-out angle 307 can additionally or alternatively comprise a lower winglet, to optimize the [...]. Similarly [...] 304 can comprise a certain and the upper can have a winglet [...]toe-out angle. The 307 has a positive sweep angle on lower winglet, and in particular the leading edge is swept back positively. The upper 304 is also positive and has a positive-swept winglet a positively-swept trailing edge and leading edge swept back on.

[0071] Fallsground spacer borders Allow it the, 307 by an uneven lower [...][...] could the lower, similar to the above described with reference to Figure 7, be replaced.

[0072] Figure 9 illustrates a combination of aircraft-Aerofoil and wing final device , comprising a wing 401, 404 and 407 an integrated upper winglet 401 has an outboard end a planar lower winglet 403 on. and defines a plane of the flap wing The 408 414 404 includes a substantially planar portion. The upper winglet and an integrated transition region 415 a. 401 403 415 Transition area leaves the outboard end of the aerofoil in the substantially plane portion 404 414 of the upper winglet uniformly extend. Transition area 415 is an uneven curved wing final extension , the continually increase in curvature of the local dihedral, a continuously increasing positive Sweep (also at the trailing edge on both the [...]) and has a continuously decreasing in the chord outboard direction. The uneven curved resistance achievementwing end -extension region 404 415 ensures an improved as compared to the in Figure 8 for the upper winglet shown integrated upper winglet 304.

[0073] The 410 409 404 has a root and an end on upper winglet. The substantially planar portion 414 404 has a angle of inclination of around 7° to the winglet of the upper vertical x-z-plane on. A substantially planar lower winglet is on the lower surface of said uneven curved 407 415 404 fixed wing end -elongation range of the upper winglet. 407 412 411 and a root end has a winglet The lower on. The root-chord of the lower with the upper winglet 404 407 intersects winglet, projects downwardly from the interface and the lower winglet.

[0074] A included angle between the upper and lower winglet 404, 407 at the interface is approximately 86°. As the interface 415 wing end -elongation range on the lower surface of the uneven curved 404 is located the upper winglet is this angle from a local surface tangent for lower surface of the uneven curved wing end -elongation range measured 415 at the interface. This included angle is preferably greater than 80 °, about 404 winglet overlapping effects between the upper and lower, to avoid 407. A included angle between the plane of the flap 124° is 408 and the lower winglet round. 404 405 409 The end substantially span border intones the winglet of the upper in the vertical x -411 407 match with the end of the lower winglet z-plane.

[0075] Figure 10 and 11 illustrate a perspective view and a plan view of the combination of the fourth embodiment and airplane wingwing final device. From Figure 10 in particular is to be seen that the rear edge 416 404 407 417 of the lower and the rear edge of the upper winglet at the interface are substantially adjacent winglet. The trailing edges 416, 417 are sufficiently close, 407 that the encounters substantially not with the flow from the lower winglet 404 superimposed on over the upper winglet. 418 404 has a leading edge on The upper winglet is a slant, the positively, and 419 407 likewise has a leading edge on the lower winglet is a slant, the positively. The trailing edge 404 is positive a slant, 416 of the upper winglet, 407 417 of the lower and the rear edge is also positive a slant, winglet.

[0076] Figure 11 illustrates the plan view (i.e., the view from top to bottom in the x-y-plane), as the upper part of the lower "shadows" 404 407 winglet at least one winglet.

[0077] This is for the compliance of the ends 409, 411 of the upper and lower winglet 404, 407 in the vertical x-y-plane due. As best in Figure 10 can be seen, Notes the at the interface 407 412 of the lower winglet root-chord only part of the local chord of the upper winglet a 404. Ups and the near conformity of trailing edges 416, 417 407 419 is substantially behind the leading edge the leading edge 418 of the upper of the lower winglet 404 arranged winglet.

[0078] Figure 12 illustrates a fifth embodiment, and a combination of aircraft-Aerofoil wing final device according, comprising a wing with a wing final device 501, 504 507 having an upper and a lower planar winglet comprises wing final extension uneven. 503 501 has an outboard end on and defines a plane of the flap wing The 508 510 504 has a root wing final extension. and an end 509 uneven The on 501 510 503 of the aerofoil and is fixed by its root at the outboard end. The 504 has a continuously increasing curvature of the local dihedral wing final extension uneven, a continuously increasing positive Sweep (both on the [...] also at the trailing edge 518, 516) and a in the outboard direction , y, continuously decreasing chord on.

[0079] The 510 504 is substantially from the root wing final extension uneven 509 uneven until the end. An inclination angle of 8° with the forms 509 The end approximately vertical x- [...]. 507 512 511 and a root end has a winglet It should be noted that the low on, and the chord intersects with the uneven curved wing final extension 504, 507 projects downwardly from the interface wherein the lower winglet. A included angle is between approximately 82 wing final extension 507 504 and the lower winglet the said uneven °. 507 and a local surface tangent is This angle between the lower to the lower surface of the uneven winglet wing final extension measured at the interface 504 curved. A included angle between the chord plane 508 507 is about 126° and the lower winglet. The ends 509, 504 and 507 511 of the uneven curved wing final extensionspan border 506 in the vertical on the vote of the lower winglet x-z-plane substantially match.

[0080] Figure 13 illustrates the fifth embodiment in a perspective view and shows clearly wing final device after the that the trailing edge 516 of the uneven curved wing final extension 504 507 517 at the intersection substantially coincides with the rear edge of the winglet. Both the uneven face 507 504 and the lower winglet wing final extension curved on a positive sweep angle, and the front and the rear edges 516, 517, 518, 519 each have a corresponding positive sweep angle on.

[0081] The lower winglet can be substantially planar and 507 can only [...][...]toe-out angle from the root towards the end a and a have in relation to the free flow stream. Similarly wing final extension[...]toe-out angle[...] and a can the uneven curved in relation to the free flow stream 504 have a. The lower winglet by a substantially uneven curved lower winglet 507 can, similarly to the above described with reference to Figure 7, be replaced, if the Allow ground headroom borders.

[0082] Any with reference to Figure by the above 7 to 13 described second to fifth embodiments is shown with the respective combination of aerofoil and in its base mold wing final device. Aerodynamic loads on the aerofoil during flight is Because of the deformation of the aerofoil wing final devicewing root cause the rotation of the so that the end of the lower wing-like element extends in the spanwise direction further than the end of the upper wing-like element overboard. The lower wing-like element Therefore, in each case an increase in the span of guaranteed, compared with the wing final devices , have in each case, only the upper wing-like element.

[0083] in the first to fifth embodiments described can at the outboard end wing final devices The an aircraft wing, the wing final device has either no, or as a substitute for an existing wing final device installed or be retrofitted. The lower wing-like element as a [...] Furthermore can"

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wing final devicethe one which can be re-tooled modification for an existing, the only element has an upper wing-like , are provided, so as to form a wing final device according to this invention.

[0084] although the invention has been described with reference to one or more preferred embodiments above to be there is that various changes or modifications can be made, without depart from the scope of the invention, as defined by the appended claims is defined.