CN202541831U - Aircraft winglet - Google Patents
Aircraft winglet Download PDFInfo
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- CN202541831U CN202541831U CN 201120395637 CN201120395637U CN202541831U CN 202541831 U CN202541831 U CN 202541831U CN 201120395637 CN201120395637 CN 201120395637 CN 201120395637 U CN201120395637 U CN 201120395637U CN 202541831 U CN202541831 U CN 202541831U
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- 238000005516 engineering process Methods 0.000 description 3
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- 238000005452 bending Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
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- 238000012986 modification Methods 0.000 description 1
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Abstract
A winglet for an aircraft, wherein the height of the winglet is 10% of the half span length of the wing, the winglet leading edge sweep angle is 1.5 times the wing leading edge sweep angle, the winglet trailing edge sweep angle is 4 times the wing trailing edge sweep angle, the winglet cant angle is 20 degrees, and the winglet installation angle is-2.6 degrees. The utility model discloses a winglet can block the upward surface of wing lower surface air current and flow around, has weakened the intensity of wingtip vortex, has increased the effective aspect ratio of wing.
Description
Technical field
The utility model relates to aviation pneumatics field, more particularly, relates to a kind of wing tip winglet of aircraft.
Background technology
In aircraft flight, the higher-pressure region air-flow of wing lower surface can be walked around wingtip and flow to upper surface, forms strong vortex at the end of wing; They have taken away energy; Brought out big induced drag simultaneously, had a strong impact on the flight efficiency of aircraft, even can bring the flight safety problem.
In order to overcome above-mentioned defective, eliminate aloft danger, improve flight efficiency, since the forties in last century, technical personnel is developed some technology successively to eliminate or to weaken above-mentioned vortex.Winglet is exactly a solution, and it is through aerodynamic configuration design, weakens the flow-disturbing of the terminal air-flow of wing, and dissipation wing tip whirlpool reduces the induced drag of aircraft, makes aircraft obtain big as far as possible drag-reduction effect, and improves 1ift-drag ratio.
In recent decades, each aircraft industry developed country of the world all is being the unremitting effort of development wing tip device, and has designed various dissimilar wing tip devices.
According to the shape of wing tip device, have several types in the world at present: a kind of is the wing tip sail, or deserves to be called trans wing tip winglet.The wing tip winglet of this style generally has the structure of syllogic; Promptly have construction section, arc transition section and straight plate section; This wing tip device has apparent in view crooked fin; In practical application, the 747-400 type aircraft that Boeing (Boeing) produces and the A330 and the A340 series aircraft of space truck (AIRBUS) have all used such wing tip device.When reequiping, this wing tip device can be installed also in addition like Boeing 727, Boeing 757 and Boeing-767 aircraft.
Another kind is a triangle wing tip sail, and the wing tip sail of this form aloft uses among passenger vehicle A320 series, A310 and the A380, also can the say so standard form of Airbus aircraft of such wing tip device.
In addition, newly-designed passenger plane of Boeing such as Boeing 777, Boeing 787, Boeing-747-8 all replace the wing tip sail with special shark fin type wing tip device (raked winglet).
Yet the aspect ratio of general aircraft is big more, and induced drag is more little, but structural weight increases thereupon, and this obviously is unfavorable for the flight of aircraft.
The utility model content
The utility model relates to a kind of aircraft winglet, and it can weaken the flow-disturbing of the terminal air-flow of wing, dissipation wing tip whirlpool guaranteeing to reduce the induced drag of aircraft under the less relatively situation of aircraft wing wing root bending.
For realizing above-mentioned purpose; The utility model provides a kind of aircraft winglet; The height of said winglet is about 10% of wing half an exhibition length, and said winglet leading edge sweep is about 1.5 times at leading edge of a wing sweepback angle, and said winglet trailing sweep is about 4 times at trailing edge sweepback angle; The winglet leaning angle is approximately 20 degree, and the winglet stagger angle is approximately got-2.6 degree.Especially, said winglet is last trans winglet.
Wherein stagger angle is the root chord line of winglet and the angle between the wing chordwise.
The winglet of the utility model is last transconfiguration, and the effect that it has the wing tip end plate stops that wing lower surface air-flow to the streaming of upper surface, has weakened the intensity in wing tip whirlpool, has increased effective aspect ratio of wing.Can not increase the actual span of wing basically, and reach same aerodynamic force effect, shut down the difficulty that the storehouse span is not enough and transfer on ground thereby solve.The distortion flow field of going up trans winglet wing tip capable of using simultaneously produces inside side force, can increase airfoil lift and forward thrust is provided.
Description of drawings
Fig. 1 is the front view of the utility model embodiment;
Fig. 2 is the scheme drawing of the utility model embodiment, and wherein winglet is connected with wing.
The specific embodiment
As shown in Figure 1, the winglet 1 of the utility model is respectively height, leading edge sweep, trailing sweep, leaning angle, the stagger angle of winglet mainly by 5 parameter determining, and wherein concrete parameter is:
1) according to the long height of confirming winglet 1 of partly exhibition of wing, the height of said winglet 1 is about 10% of wing 2 half exhibition length, and in the present embodiment, wing 2 half exhibition length are 12 meters, and the winglet height is 1.25 meters;
2) leading edge sweep of winglet 1 confirms that according to the leading edge sweep of wing 2 said winglet 1 leading edge sweep is about 1.5 times of wing 2 leading edge sweeps, and in the present embodiment, wing 2 leading edge sweeps are 27 degree, and the winglet leading edge sweep is 40 degree;
3) trailing sweep of winglet 1 confirms that according to the trailing sweep of wing 2 said winglet 1 trailing sweep is about 4 times of wing 2 trailing sweeps, and in the present embodiment, wing 2 trailing sweeps are 17 degree, and winglet 1 trailing sweep is 67 degree;
4) in the present embodiment, winglet 1 leaning angle is got 20 degree;
5) in the present embodiment, winglet 1 stagger angle is got-2.6 degree.
In addition, in the present embodiment, the winglet aerofoil profile is a supercritical airfoil.
The technology contents and the technical characterstic of the utility model disclose as above, yet are appreciated that under the creative ideas of the utility model, those skilled in the art can make various changes and modifications to said structure, but all belongs to protection scope of the present invention.The description of the foregoing description is exemplary rather than restrictive, and the protection domain of the utility model is confirmed by claim.
Claims (3)
1. an aircraft winglet is characterized in that, the height of said winglet is 10% of wing half an exhibition length; Said winglet leading edge sweep is 1.5 times at leading edge of a wing sweepback angle; Said winglet trailing sweep is 4 times at trailing edge sweepback angle, and the winglet leaning angle is 20 degree, and the winglet stagger angle is got-2.6 degree.
2. winglet as claimed in claim 1 is characterized in that, said winglet aerofoil profile is a supercritical airfoil.
3. according to claim 1 or claim 2 winglet is characterized in that said winglet is last trans winglet.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120395637 CN202541831U (en) | 2011-10-18 | 2011-10-18 | Aircraft winglet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120395637 CN202541831U (en) | 2011-10-18 | 2011-10-18 | Aircraft winglet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202541831U true CN202541831U (en) | 2012-11-21 |
Family
ID=47162502
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120395637 Expired - Lifetime CN202541831U (en) | 2011-10-18 | 2011-10-18 | Aircraft winglet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202541831U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103625634A (en) * | 2013-12-17 | 2014-03-12 | 中国航天空气动力技术研究院 | Detachable wingtip winglet device with adjustable dip angles |
| CN106394866A (en) * | 2016-11-21 | 2017-02-15 | 顺丰科技有限公司 | Wing of unmanned aerial vehicle and unmanned aerial vehicle |
| 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 |
-
2011
- 2011-10-18 CN CN 201120395637 patent/CN202541831U/en not_active Expired - Lifetime
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103625634A (en) * | 2013-12-17 | 2014-03-12 | 中国航天空气动力技术研究院 | Detachable wingtip winglet device with adjustable dip angles |
| CN106394866A (en) * | 2016-11-21 | 2017-02-15 | 顺丰科技有限公司 | Wing of unmanned aerial vehicle and unmanned aerial vehicle |
| 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 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121121 |
|
| CX01 | Expiry of patent term |