CN206050054U - The wingtip device of aircraft wing - Google Patents
The wingtip device of aircraft wing Download PDFInfo
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- CN206050054U CN206050054U CN201620901774.6U CN201620901774U CN206050054U CN 206050054 U CN206050054 U CN 206050054U CN 201620901774 U CN201620901774 U CN 201620901774U CN 206050054 U CN206050054 U CN 206050054U
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- winglet
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- wingtip device
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C23/00—Influencing air flow over aircraft surfaces, not otherwise provided for
- B64C23/06—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices
- B64C23/065—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips
- B64C23/069—Influencing air flow over aircraft surfaces, not otherwise provided for by generating vortices at the wing tips using one or more wing tip airfoil devices, e.g. winglets, splines, wing tip fences or raked wingtips
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Abstract
This utility model provides a kind of wingtip device of aircraft wing, is symmetrically disposed in the wing tip portion of the both sides wing of aircraft, it is characterised in that be provided with the outside of the wing tip portion of every side wing：Upper winglet, upper winglet connect along the wing length directional smoothing, and are bent upwards tilting；Winglet, the winglet is directly connected with the lower surface of the upper winglet, length between the junction of the junction of the winglet and the upper winglet to the upper winglet and the end face outside in the wing tip portion accounts for the 20% to 75% of the length of the whole upper winglet, and the winglet is bent upwards, horizontal stretching or be bent downwardly；Lower winglet, the lower winglet are also directly connected with the lower surface of the upper winglet, and the lower winglet is bent downwardly along the wing length direction.This utility model can efficiently reduce the intensity of aircraft wing point vortex, reduce the shock strength on three winglets, and airflow design is more favorable to reduce resistance.
Description
Technical field
This utility model is related to a kind of wingtip device of aircraft wing, in particular for the wingtip device of aircraft main wing.
Background technology
With requirement more and more higher of the modern Ci vil Aircraft Design to drag reduction, the single winglet of tradition is as above trans, shark
The wingtip device such as fin and eddy diffusion device can not meet pneumatic design requirement.It is more multiple that aircraft designers start design
Miscellaneous wingtip device, in the hope of obtaining more preferable drag-reduction effect.Fig. 1 is the double pinniform wingtip devices used on B737MAX, compares biography
The upper trans winglet of system, has added wing tip winglet directed downwardly in lower aerofoil.Winglet directed downwardly can stop lower aerofoil
Open up to air-flow, weaken the intensity of the vortex of whole wing tip；And its vortex for producing is mutual with the vortex that winglet upward is produced
Mutually suppress, make the intensity decreases of the vortex of whole wing tip, so as to reduce induced drag.But in double pinniform wingtip devices, its
Relatively far away from, the effect that the vortex of generation suppresses mutually is weaker, and the drag-reduction effect of acquirement is limited for two winglets upwardly and downwardly.
Meanwhile, double pinniform tip designs also carry various corner angle, increased the resistance of aircraft wing.
Utility model content
In order to solve above-mentioned technical problem, effectively weaken the vortex in aircraft wing wing tip portion, and reduce aircraft wing resistance
Power, this utility model provide a kind of wingtip device of aircraft wing, are symmetrically disposed in the wing tip portion of the both sides wing of aircraft,
Characterized in that, being provided with the outside of the wing tip portion of every side wing：
Upper winglet, the end face outside in upper winglet root portion and the wing tip portion is along the wing length directional smoothing
Connection, and the upper winglet is bent upwards tilting along the wing length direction；
Winglet, the winglet are directly connected with the lower surface of the upper winglet, the winglet and the upper winglet
Junction to the upper winglet and the end face outside in the wing tip portion junction between length account for it is whole it is described on
The 20% to 75% of the length of winglet, the winglet is bent upwards along the wing length direction, horizontal stretching or downward
Bending；
Lower winglet, the lower winglet are also directly connected with the lower surface of the upper winglet, and the lower winglet is little with described
The junction of the wing than the winglet and the upper winglet junction closer to the upper winglet and the wing tip portion
The junction of end face outside, the lower winglet are bent downwardly along the wing length direction.
Preferably, wingtip device of the wingtip device of the aircraft wing for aircraft main wing.
Preferably, the winglet with the junction of the upper winglet to the upper winglet and the wing tip portion
Length between the junction of end face outside accounts for the 30% to 60% of the length of the whole upper winglet.
Preferably, the winglet and the lower winglet are and the dismountable part of the upper winglet, the winglet
It is detachably connected on the correspondence position of the upper winglet lower surface with the lower winglet.
Preferably, on described on the length direction of winglet, the lower winglet is with the winglet close to arrangement.
Preferably, on described on the length direction of winglet, the lower winglet is whole with the winglet neighbor distance
The 0% to 15% of the length of the individual upper winglet.
Preferably, winglet wing root portion incisal plane is designated as γ 1 with the angle of wing place plane, the angle γ's 1
Span is：-15°≤γ1≤15°；Upper winglet incisal plane of the winglet at upper winglet position is located flat with wing
The angle in face is designated as α 1, and the span of the angle α 1 is：10°≤α1≤45°；Lower winglet is at upper winglet position
Upper winglet incisal plane is designated as β 1 with the angle of wing place plane, and the span of the angle β 1 is：10°≤β1≤45°.
It is highly preferred that winglet wing root portion incisal plane is designated as γ 1 with the angle of wing place plane, the angle γ's 1
Span is：-5°≤γ1≤5°；Upper winglet incisal plane of the winglet at upper winglet position and wing place plane
Angle be designated as α 1, the span of the angle α 1 is：10°≤α1≤45°；Lower winglet is upper at upper winglet position
Winglet incisal plane is designated as β 1 with the angle of wing place plane, and the span of the angle β 1 is：10°≤α1≤β1≤45°.
Preferably, winglet wing tip portion incisal plane is designated as γ 2 with the angle of wing place plane, the angle γ's 2
Span is：-15°≤γ2≤15°；Upper winglet wing tip portion incisal plane is designated as α 2, the folder with the angle of wing place plane
The span of angle α 2 is：90 ° of 10 °≤α, 2 ＜；Lower winglet wing tip portion incisal plane is designated as β 2, institute with the angle of wing place plane
The span for stating angle β 2 is：90 ° of 10 °≤β, 2 ＜.
It is highly preferred that winglet wing tip portion incisal plane is designated as γ 2 with the angle of wing place plane, the angle γ's 2
Span is：-5°≤γ2≤5°；Upper winglet wing tip portion incisal plane is designated as α 2, the angle with the angle of wing place plane
The span of α 2 is：90 ° of 10 °≤α, 1≤α, 2 ＜；Lower winglet wing tip portion incisal plane is designated as β 2 with the angle of wing place plane,
The span of the angle β 2 is：90 ° of 10 °≤β, 1≤β, 2 ＜.
Preferably, the ratio that medium and small chord-length accounts for upper winglet local chord of the winglet at upper winglet position is
60% to 90%；Under little chord-length account for upper winglet local chord of the lower winglet at upper winglet position ratio be 60% to
90%.
Preferably, winglet wing root trailing edge and/or lower winglet root trailing edge, are overlapped with upper winglet trailing edge.
Preferably, medium and small chord-length is less than down little chord-length.
Preferably, the upper little nose of wing and the leading edge of a wing be to be smoothly connected, and/or the upper winglet trailing edge with
The trailing edge is to be smoothly connected.
Preferably, the torsion angle in the upper winglet root portion is identical with the torsion angle in the wing tip portion.
Preferably, the upper winglet is the shark fin type winglet blended with the wing tip portion.
Preferably, the upper little nose of wing, and/or the medium and small nose of wing, and/or it is described under little nose of wing, in big
The SPL of sweepback.
Preferably, the upper winglet trailing edge using with the upper little nose of wing identical SPL, and/or it is described in
Winglet trailing edge using with the medium and small nose of wing identical SPL, and/or the lower winglet trailing edge using with it is described under it is little
Nose of wing identical SPL.
Preferably, the upper winglet, and/or the winglet, and/or the lower winglet, using supercritical airfoil.
The wingtip device of aircraft wing of the present utility model, than adding in the middle of two separate wing tips of double pinniform wing tips
One middle wing tip equivalent to aircraft wing extension, so as to define three winglets from top to bottom.These three winglets are produced
Vortex apart from relative close, and there is strong mutual suppression between the vortex of three generations so that whole aircraft wing
The intensity of tip vortex is greatly lowered.At the same time, the wingtip device of aircraft wing of the present utility model employs streamlined setting
Meter, is more beneficial for reducing resistance.Thus, compared to double pinniform wingtip devices, the wingtip device of aircraft wing of the present utility model
Possess more preferable drag reduction capability.
Description of the drawings
Fig. 1 is the wingtip device of aircraft wing of the prior art.
Fig. 2 is the schematic perspective view of the wingtip device of preferred aircraft wing of the present utility model.
Fig. 3 is the three-dimensional signal that the wingtip device of preferred aircraft wing of the present utility model is observed from another angle
Figure.
Fig. 4 is the front view of the wingtip device of the of the present utility model preferred aircraft wing in Fig. 2.
Fig. 5 is the left view of the wingtip device of the of the present utility model preferred aircraft wing in Fig. 2.
Fig. 6 is the top view of the wingtip device of the of the present utility model preferred aircraft wing in Fig. 2.
Fig. 7 is the interaction of the wingtip vortex of three winglets of the wingtip device of preferred aircraft wing of the present utility model
Principle schematic.
Fig. 8 is the tangential of the wing root portion leading edge of three winglets of the wingtip device of preferred aircraft wing of the present utility model
Position view.
Fig. 9 is that the relative position of each winglet in the wingtip device of preferred aircraft wing of the present utility model is illustrated
Figure.
Figure 10 is that the wing root portion angle of each winglet in the wingtip device of preferred aircraft wing of the present utility model shows
It is intended to.
Figure 11 is that the wing tip portion angle of each winglet in the wingtip device of preferred aircraft wing of the present utility model shows
It is intended to.
Figure 12 is the schematic diagram of each the detachable winglet in the wingtip device of preferred aircraft wing of the present utility model.
Specific embodiment
This utility model is described in further detail below in conjunction with accompanying drawing and instantiation.For the convenience discussed,
Using " on ", D score, "left", "right" the orientation in each schematic diagram is indicated, be conducive to the expansion discussed.According to this reality
The characteristics of using new, specific embodiment are used in illustrating the coordinate system of XYZ, and some accompanying drawings behind in fig. 2
XOY faces view, YOZ faces view, ZOX faces view are arrived, when these accompanying drawings are read, can have been carried out with reference to the axonometric chart in Fig. 2
Understand.
As shown in Fig. 2 being the wingtip device preferred embodiment of aircraft wing of the present utility model, especially, it is aircraft master
The wingtip device preferred embodiment of the wing.Even so, it will be appreciated by those skilled in the art that the technical solution of the utility model
Can be used on empennage, can correspondingly be applied according to the size of empennage.
As shown in Figures 2 and 3, with reference to preferred aircraft main wing of the present utility model forward sight Fig. 4 of wingtip device, left view
Fig. 5, Fig. 6 is overlooked, illustrate the main wing 1 of aircraft side, it is to be understood that be symmetrical with this in the main wing of aircraft opposite side.
As shown in Figures 2 to 6, the outside in the wing tip portion 100 of main wing 1 is provided with winglet 2, winglet 3, lower winglet 4.
Preferably, each winglet, using supercritical airfoil.
As in Fig. 2 to Fig. 6, the end face outside in upper winglet root portion 210 and main wing wing tip portion 100 is along main wing length direction
Smooth connection, and upper winglet 2 is bent upwards tilting along main wing length direction.As shown in Figures 2 and 3, it is little thriving for upper
The section of root 210, is described using perspective view, shows contour line 211 on the upper winglet root portion section in Fig. 2 or 3
With upper winglet root portion section lower contour 212.Contour line 211 and upper winglet root portion on upper winglet root portion section herein
Section lower contour 212 is the needs for showing, in fact, in actual part, be smooth continuous transition herein.
As shown in Figures 2 to 6, winglet 3 is directly connected with the lower surface of upper winglet 2, with reference to shown in Fig. 9, winglet 3 with
Length L3 between the junction of the end face outside of the supreme winglet 2 in junction and main wing wing tip portion 100 of upper winglet 3 is accounted on whole
The 20% to 75% of length L2 of winglet 2, it may be preferred to for 30% to 60%.Winglet 3 can be to along main wing length direction
Upper bending, horizontal stretching are bent downwardly, and can be selected according to actual needs.From Fig. 2, for winglet wing root portion
310 section, is described using perspective view, shows contour line 311 and winglet on the winglet wing root section in Fig. 2
Wing root section lower contour 312.
As shown in Fig. 2 to Fig. 6, lower winglet 4 is also directly connected with the lower surface of upper winglet 2, lower winglet 4 and upper winglet 2
Junction than winglet 3 and upper winglet 2 junction closer to upper winglet 2 and the end face outside in main wing wing tip portion 100 company
Place is met, lower winglet 4 is bent downwardly along main wing length direction.In fig. 2, for the section in lower winglet root portion 410, using saturating
View is described, and shows contour line 411 and lower winglet root portion section bottom profiled on the lower winglet root portion section in Fig. 2
Line 412.
As shown in Figures 2 to 6, upper winglet 2 and main wing 1 are designed for fusion type, wherein above winglet 2 as with main wing 1
Main connector, it is ensured that the pressure distribution form of main wing upper surface is not destroyed, while upper winglet 2 adopts fusion with main wing 1
Formula design can be installed to upper winglet 2 corresponding position as bearing member winglet 3 and lower winglet 4 using more convenient.
According to Fig. 2 and with reference to shown in Figure 12, it will be understood that winglet 3 with lower winglet 4 is and 2 dismountable portion of upper winglet
Part, winglet 3 are detachably connected on the correspondence position of 2 lower surface of upper winglet with lower winglet 4.As shown in figures 4 and 9, one
Planting preferred method for arranging is, on the length direction of upper winglet 2, lower winglet 4 is could be arranged to close to arrangement with winglet 3；
Another kind of preferred method for arranging is, on the length direction of upper winglet 2, lower winglet 4 is on whole with 3 neighbor distance of winglet
The 0% to 15% of the length of winglet.In both preferred arrangements, can in view of on the premise of structural agent,
So that close to arrangement more effectively, winglet 3, is conducive to better profiting from the wing in above-mentioned Fig. 7 close to arrangement with lower winglet
The interaction principle of sharp air whirl, for this principle can be described in detail after.As shown in Fig. 2 each winglet herein
Be not simple " inserting " on main wing 1, but main wing 1 is connected smoothly by curved surface, realizes the design of fusion type, reduction
Blunt form transition may caused by resistance.
As can be known from Fig. 12, there is the method for two kinds of assemblings, first method is detachable winglet 3 and lower winglet
4 correspondence positions for being first installed to winglet 2, form a fixed entirety, upper winglet 2 are installed on main wing 1；Second method
It is that upper winglet 2 is first installed on main wing 1, detachable winglet 3 is installed to upper winglet 2 with lower winglet 4 again then
Correspondence position.Both assembly methods are all feasible, can be assembled as the case may be.
As shown in figure 8, illustrating the wing root of three winglets of the wingtip device of preferred aircraft main wing of the present utility model
The chordwise location schematic diagram of portion's leading edge.Medium and small chord-length 35 accounts for upper winglet locality string of the winglet 3 at 2 position of upper winglet
Long 235 ratio is 60% to 90%；Under little chord-length 45 to account for upper winglet of the lower winglet 4 at 2 position of upper winglet local
The ratio of chord length 245 is 60% to 90%.With reference to shown in Fig. 2, aircraft main wing 1 is preferably designed using fusion type with upper winglet 2, on
Winglet 2 can be considered the extension of aircraft main wing 1, as shown in figure 8, the little chord-length 45 with of medium and small chord-length 35 can be accounted for respectively and be worked as
The ratio of ground chord length is identical, and certain being between 60% to 90% determines numerical value, and medium and small chord-length 35 is less than down little wing chord
Long 45.
With reference to shown in Fig. 6, winglet wing root trailing edge 39 and lower winglet root trailing edge 49 are overlapped with upper winglet trailing edge 29,
With main wing leading edge 18 to be smoothly connected, upper winglet trailing edge 29 is also to be smoothly connected with main wing trailing edge 19 to upper little nose of wing 28.It is upper little
Cautiously the torsion angle of root 29 is identical with the torsion angle in main wing wing tip portion 100.Upper winglet 2 is to blend with main wing wing tip portion 100
Shark fin type winglet, upper little nose of wing 28, medium and small nose of wing 38, under little nose of wing 48, the SPL in big sweepback.On
Winglet trailing edge 29 is adopted and 28 identical SPL of upper little nose of wing, and winglet trailing edge 39 is using identical with medium and small nose of wing 38
SPL, lower winglet trailing edge 49 is using the 48 identical SPL of little nose of wing with.Three winglets adopt big sweepback
Distribution form, airflow design is also more sophisticated, and adopts supercritical airfoil, effectively can reduce on three winglets
Shock strength, reduce resistance, reduce vortex.
As shown in Figure 10, illustrate the wing of each winglet in the wingtip device of preferred aircraft main wing of the present utility model
Root angle schematic diagram.Winglet wing root portion incisal plane is designated as γ 1 with the angle of main wing place plane, and angle γ's 1 preferably takes
Value scope is：-15°≤γ1≤15°；The more preferably span of angle γ 1 is, 1≤5 ° of -5 °≤γ.Very especially, here
In preferred embodiment, angle γ 1=0 °, in this case, winglet wing root portion incisal plane is just parallel with main wing place plane.
The angle of upper winglet incisal plane of the winglet 3 at 2 position of upper winglet and main wing place plane is designated as α 1, and angle α 1 takes
Value scope is：10°≤α1≤45°.Upper winglet incisal plane of the lower winglet 4 at 2 position of upper winglet and main wing place plane
Angle be designated as β 1, the span of angle β 1 is：The more preferably span of 1≤45 ° of 10 °≤β, angle β 1 is：10°≤α1
≤β1≤45°。
As shown in figure 11, illustrate the wing of each winglet in the wingtip device of preferred aircraft main wing of the present utility model
Tip angle schematic diagram.Winglet wing tip portion incisal plane is designated as γ 2, the value model of angle γ 2 with the angle of main wing place plane
Enclosing is：The more preferably span of 2≤15 ° of angle γ 2 of -15 °≤γ is, 2≤5 ° of -5 °≤γ.Upper winglet wing tip portion incisal plane
α 2 is designated as with the angle of main wing place plane, the span of angle α 2 is：90 ° of 10 °≤α, 2 ＜, the more preferably value of angle α 2
Scope is：10 °≤α, 1≤α, 2 ＜, 90 ° of lower winglet wing tip portion incisal planes are designated as β 2 with the angle of main wing place plane, angle β's 2
Span is：90 ° of 10 °≤β, 2 ＜, the more preferably span of angle β 2 is：90 ° of 10 °≤β, 1≤β, 2 ＜.
As shown in fig. 7, illustrating the wing tip of three winglets of the wingtip device of preferred aircraft wing of the present utility model
The interaction principle schematic diagram in whirlpool.Three winglets design on main wing wing tip 1, arrange from top to bottom three it is independent
Winglet, each winglet can produce wingtip vortex.As shown in Figure 7, the direction of rotation of the stream swirl in the wing tip portion of three winglets
It is identical, therefore, when three winglets wing tip portion generally in from it is upper arrange down when, the vortex side below upper winglet wing tip portion 26
To in opposite direction with the vortex above winglet wing tip portion 36, so as to formed air-flow mutually suppress or counteracting gesture.In the same manner, it is medium and small
Vortex direction cautiously below tip 36 is in opposite direction with the vortex above lower winglet wing tip portion 46, mutual so as to also form air-flow
Suppression or the gesture of counteracting.As different stream swirls suppress mutually or offset, the stream swirl of whole wing tip is effectively reduced
Intensity, and then substantially reduce wing tip portion resistance.
Described above to embodiment, enables professional and technical personnel in the field to realize or use this utility model.To reality
The various modifications for applying example will be apparent for those skilled in the art, generic principles defined herein
Can be realized in the case of without departing from spirit or scope of the present utility model in other embodiments.Therefore, this utility model
It is not intended to be limited to embodiment illustrated herein, all technical sides obtained by the way of equivalent or equivalent transformation
Case, all falls within protection domain of the present utility model.It is only the preferred embodiment of utility model in sum, is not used for
Limit practical range of the present utility model.The equivalence changes made by i.e. all contents according to this utility model claim with repair
Decorations, all should be technology category of the present utility model.
Claims (19)
1. a kind of wingtip device of aircraft wing, is symmetrically disposed in the wing tip portion of the both sides wing of aircraft, it is characterised in that
It is provided with the outside of wing tip portion per side wing：
Upper winglet, upper winglet root portion are connected along the wing length directional smoothing with the end face outside in the wing tip portion
Connect, and the upper winglet is bent upwards tilting along the wing length direction；
Winglet, the winglet are directly connected with the lower surface of the upper winglet, the company of the winglet and the upper winglet
Length between the junction at the place of connecing to the upper winglet and the end face outside in the wing tip portion accounts for the whole upper winglet
Length 20% to 75%, the winglet is bent upwards along the wing length direction, horizontal stretching or be bent downwardly；
Lower winglet, the lower winglet are also directly connected with the lower surface of the upper winglet, the lower winglet and the upper winglet
Junction than the winglet and the upper winglet junction closer to the upper winglet and the wing tip portion outside
The junction of end face, the lower winglet are bent downwardly along the wing length direction.
2. the wingtip device of aircraft wing according to claim 1, it is characterised in that the wingtip device of the aircraft wing
For the wingtip device of aircraft main wing.
3. the wingtip device of aircraft wing according to claim 1, it is characterised in that the winglet and the upper winglet
Junction to the upper winglet and the end face outside in the wing tip portion junction between length account for it is whole it is described on
The 30% to 60% of the length of winglet.
4. the wingtip device of the aircraft wing according to claim 1,2 or 3, it is characterised in that the winglet with it is described
Lower winglet is and the upper winglet dismountable part that the winglet is detachably connected to described little with the lower winglet
On the correspondence position of wing lower surface.
5. the wingtip device of the aircraft wing according to claim 1,2 or 3, it is characterised in that the length of winglet on described
On degree direction, the lower winglet is with the winglet close to arrangement.
6. the wingtip device of the aircraft wing according to claim 1,2 or 3, it is characterised in that the length of winglet on described
On degree direction, the lower winglet and the 0% to 15% of the length that the winglet neighbor distance is the whole upper winglet.
7. the wingtip device of aircraft wing according to claim 1, it is characterised in that
Winglet wing root portion incisal plane is designated as γ 1 with the angle of wing place plane, and the span of the angle γ 1 is：-
15°≤γ1≤15°；
Upper winglet incisal plane of the winglet at upper winglet position is designated as α 1, the angle with the angle of wing place plane
The span of α 1 is：10°≤α1≤45°；
Upper winglet incisal plane of the lower winglet at upper winglet position is designated as β 1, the angle with the angle of wing place plane
The span of β 1 is：10°≤β1≤45°.
8. the wingtip device of aircraft wing according to claim 7, it is characterised in that
Winglet wing root portion incisal plane is designated as γ 1 with the angle of wing place plane, and the span of the angle γ 1 is：-5°
≤γ1≤5°；
Upper winglet incisal plane of the winglet at upper winglet position is designated as α 1, the angle with the angle of wing place plane
The span of α 1 is：10°≤α1≤45°；
Upper winglet incisal plane of the lower winglet at upper winglet position is designated as β 1, the angle with the angle of wing place plane
The span of β 1 is：10°≤α1≤β1≤45°.
9. the wingtip device of the aircraft wing according to claim 7 or 8, it is characterised in that
Winglet wing tip portion incisal plane is designated as γ 2 with the angle of wing place plane, and the span of the angle γ 2 is：-
15°≤γ2≤15°；
Upper winglet wing tip portion incisal plane is designated as α 2 with the angle of wing place plane, and the span of the angle α 2 is：10°≤
90 ° of 2 ＜ of α；
Lower winglet wing tip portion incisal plane is designated as β 2 with the angle of wing place plane, and the span of the angle β 2 is：10°≤
90 ° of 2 ＜ of β.
10. the wingtip device of aircraft wing according to claim 9, it is characterised in that winglet wing tip portion incisal plane with
The angle of wing place plane is designated as γ 2, and the span of the angle γ 2 is：-5°≤γ2≤5°；
Upper winglet wing tip portion incisal plane is designated as α 2 with the angle of wing place plane, and the span of the angle α 2 is：10°≤
90 ° of 1≤α of α, 2 ＜；
Lower winglet wing tip portion incisal plane is designated as β 2 with the angle of wing place plane, and the span of the angle β 2 is：10°≤
90 ° of 1≤β of β, 2 ＜.
The wingtip device of 11. aircraft wings according to claim 1,2 or 3, it is characterised in that
It is 60% to 90% that medium and small chord-length accounts for the ratio of upper winglet local chord of the winglet at upper winglet position；
Under little chord-length to account for the ratio of upper winglet local chord of the lower winglet at upper winglet position be 60% to 90%.
The wingtip device of 12. aircraft wings according to claim 11, it is characterised in that winglet wing root trailing edge and/or
Lower winglet root trailing edge, is overlapped with upper winglet trailing edge.
The wingtip device of 13. aircraft wings according to claim 12, it is characterised in that medium and small chord-length is less than lower winglet
Chord length.
The wingtip device of 14. aircraft wings according to claim 1,2 or 3, it is characterised in that the upper little nose of wing with
The leading edge of a wing is to be smoothly connected, and/or the upper winglet trailing edge is to be smoothly connected with the trailing edge.
The wingtip device of 15. aircraft wings according to claim 1,2 or 3, it is characterised in that the upper winglet root portion
Torsion angle it is identical with the torsion angle in the wing tip portion.
The wingtip device of 16. aircraft wings according to claim 1,2 or 3, it is characterised in that the upper winglet is and institute
State the shark fin type winglet that wing tip portion blends.
The wingtip device of 17. aircraft wings according to claim 1,2 or 3, it is characterised in that the upper little nose of wing,
And/or the medium and small nose of wing, and/or it is described under little nose of wing, the SPL in big sweepback.
The wingtip device of 18. aircraft wings according to claim 17, it is characterised in that the upper winglet trailing edge using with
The upper little nose of wing identical SPL, and/or the winglet trailing edge using with the medium and small nose of wing identical sample
Bar curve, and/or the lower winglet trailing edge using with it is described under little nose of wing identical SPL.
The wingtip device of 19. aircraft wings according to claim 1,2 or 3, it is characterised in that the upper winglet, and/or
The winglet, and/or the lower winglet, using supercritical airfoil.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620901774.6U CN206050054U (en) | 2016-08-18 | 2016-08-18 | The wingtip device of aircraft wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620901774.6U CN206050054U (en) | 2016-08-18 | 2016-08-18 | The wingtip device of aircraft wing |
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| Publication Number | Publication Date |
|---|---|
| CN206050054U true CN206050054U (en) | 2017-03-29 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
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| CN201620901774.6U Active CN206050054U (en) | 2016-08-18 | 2016-08-18 | The wingtip device of aircraft wing |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN108454822A (en) * | 2018-04-28 | 2018-08-28 | 成都航空职业技术学院 | A kind of small swing device of replaceable and its change method |
| WO2019011395A1 (en) * | 2017-07-12 | 2019-01-17 | The Aircraft Performance Company Gmbh | Airplane wing with at least two winglets |
| CN110525630A (en) * | 2018-05-25 | 2019-12-03 | 北京德知航创科技有限责任公司 | Dismountable airplane wingtip winglet and its design method |
| CN111629961A (en) * | 2018-01-15 | 2020-09-04 | 航空器性能公司 | Aircraft wing |
| US20210197961A1 (en) * | 2019-12-30 | 2021-07-01 | Bombardier Inc. | Winglet systems for aircraft |
| US11279469B2 (en) | 2016-07-12 | 2022-03-22 | The Aircraft Performance Company Gmbh | Airplane wing |
| US11396368B2 (en) | 2017-12-15 | 2022-07-26 | The Aircraft Performance Company Gmbh | Airplane wing |
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2016
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11279469B2 (en) | 2016-07-12 | 2022-03-22 | The Aircraft Performance Company Gmbh | Airplane wing |
| WO2019011395A1 (en) * | 2017-07-12 | 2019-01-17 | The Aircraft Performance Company Gmbh | Airplane wing with at least two winglets |
| CN110891857A (en) * | 2017-07-12 | 2020-03-17 | 航空器性能公司 | Aircraft wing with at least two winglets |
| US11312481B2 (en) | 2017-07-12 | 2022-04-26 | The Aircraft Performance Company Gmbh | Airplane wing |
| US11396368B2 (en) | 2017-12-15 | 2022-07-26 | The Aircraft Performance Company Gmbh | Airplane wing |
| CN111629961A (en) * | 2018-01-15 | 2020-09-04 | 航空器性能公司 | Aircraft wing |
| US11427307B2 (en) | 2018-01-15 | 2022-08-30 | The Aircraft Performance Company Gmbh | Airplane wing |
| CN108454822A (en) * | 2018-04-28 | 2018-08-28 | 成都航空职业技术学院 | A kind of small swing device of replaceable and its change method |
| CN110525630A (en) * | 2018-05-25 | 2019-12-03 | 北京德知航创科技有限责任公司 | Dismountable airplane wingtip winglet and its design method |
| US20210197961A1 (en) * | 2019-12-30 | 2021-07-01 | Bombardier Inc. | Winglet systems for aircraft |
| EP3845451A1 (en) * | 2019-12-30 | 2021-07-07 | Bombardier Inc. | Winglet systems for aircraft |
| EP4223633A1 (en) * | 2019-12-30 | 2023-08-09 | Bombardier Inc. | Winglet systems for aircraft |
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