CN202953169U - Novel spoon-shaped blended winglet for civil airplane - Google Patents
Novel spoon-shaped blended winglet for civil airplane Download PDFInfo
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- CN202953169U CN202953169U CN 201220590766 CN201220590766U CN202953169U CN 202953169 U CN202953169 U CN 202953169U CN 201220590766 CN201220590766 CN 201220590766 CN 201220590766 U CN201220590766 U CN 201220590766U CN 202953169 U CN202953169 U CN 202953169U
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Abstract
本实用新型公开了一种民用客机的新型匙形融合式翼梢小翼，属于航空气动技术领域。所述的翼梢小翼选择NACA SC(2)0410翼型，翼梢小翼有四个翼型占位面，分别记为A#、B#、C#、D#翼型，其中A#为小翼翼根翼型，B#为小翼下倾翼型，C#为小翼过渡翼型，D#为小翼翼尖翼型，所述的翼梢小翼的展长为8%～12%的机翼半翼展，前缘后掠角为40°～50°，尖梢比0.28～0.34，上倾角为17°～22°，下倾角4°～7°，各占位翼型的安装角-2°～-4°。相对传统小翼，本实用新型对翼根有更小的弯矩，提高结构重量收益。诱导阻力减阻效果显著，从而改善气动特性，提高飞行经济性。显著提高飞机机翼升阻比。
The utility model discloses a novel spoon-shaped fusion type winglet of a civil airliner, which belongs to the technical field of aviation aerodynamics. The described winglet selects NACA SC(2)0410 airfoil, and the winglet has four airfoil occupying surfaces, respectively recorded as A#, B#, C#, D# airfoil, wherein A# is the root wing of the winglet type, B# is the down-tilted airfoil of the winglet, C# is the transitional airfoil of the winglet, and D# is the tip of the winglet. The edge sweep angle is 40°～50°, the tip ratio is 0.28～0.34, the uptilt angle is 17°～22°, the downtilt angle is 4°～7°, and the installation angle of each airfoil is -2°～-4° . Compared with the traditional winglet, the utility model has a smaller bending moment on the root of the wing and improves the structural weight gain. The induced drag reduction effect is remarkable, thereby improving aerodynamic characteristics and improving flight economy. Significantly improve the lift-to-drag ratio of the aircraft wing.
Description
Technical field
The invention belongs to aviation pneumatics field, be specifically related to a kind of a kind of novel winglet that induced drag installs additional at the wing wing tip when reducing aircraft flight.
Background technology
Reducing induced drag is a kind of method that reduces total drag now relatively more commonly used.Induced drag is the important component part of aircraft drag, concerning large-scale seating plane, the induced drag of aircraft accounts for 30% left and right of full machine total drag when cruising, proportion is larger than high-angle-of-attack flight the time, therefore, if can reduce the induced drag of aircraft, the operating cost of saving oil consumption and reduction aircraft is had a very big significance.
Installing winglet additional at the wing wing tip is a kind of important means that reduces the aircraft induced drag.Aircraft awing, effect due to wing upper and lower surface difference of pressure, the air-flow that flows through the wing upper and lower surface not only can be rolled at the wingtip of wing the wing-tip vortex of an anticlockwise direction rotation, and can merge into a vortex face of downbeam hauling-out backward at trailing edge.This vortex face and wing-tip vortex have formed the trailing vortex of aircraft after wing, and produce a downward induction velocity (generally being called purling) near wing.The effect of this purling just makes the air flow line that flows to wing that a downward change occur, thereby makes the resultant force vector hypsokinesis of the aerodynamic force that acts on wing.Resultant force vector component in the vertical direction is exactly lift, and component in the horizontal direction just is called induced drag.The Main Function of winglet is to reduce induced drag.After loading onto a winglet in the wing end, at first winglet plays and stops that wing lower surface air-flow is to the effect of streaming of upper surface, i.e. end plate effect.Secondly, the winglet wing-tip vortex that can dissipate, winglet also produces one very strong trailing vortex when producing lift, it and wing wing-tip vortex close proximity, two bursts of whirlpools are just in time opposite in the induction velocity direction of intersection, thereby weaken the downwash flow field of wing wingtip, and induced drag is reduced.
But installing winglet additional also has many drawbacks.It is the end that is contained in wing due to winglet, the wing root is produced a larger additional moment, can make structure and the weight of wing pay larger cost, so the pneumatic benefit that the design of winglet must will obtain and the structural weight increase that brings simultaneously and the overall balance consideration together of complete other aeroperformances of machine.
Summary of the invention
The objective of the invention is provides a kind of suitable winglet scheme for seating plane.The wing-tip vortex that produces during with the flight of diffusion civil aircraft reduces full machine resistance thereby reduce induced drag, improves its aerodynamic characteristic, improves civil aircraft flight economy; With respect to traditional winglet, configuration provided by the invention produces less additional bending moment to wing root simultaneously, and the structural weight cost is less.
The novel cochlear fusion type winglet of a kind of seating plane provided by the invention on traditional fusion type winglet basis, adds the feature that has a down dip, and makes it to become a cochlear structure; This winglet has four aerofoil profile occupy-place faces to control, and forms the winglet front and rear edge, is designated as respectively A#, B#, C#, D# aerofoil profile, and wherein A# is winglet wing root aerofoil profile, and B# is the winglet aerofoil profile that has a down dip, and C# is winglet transition aerofoil profile, and D# is winglet wing tip aerofoil profile; The B# aerofoil profile that has a down dip is controlled the size of the angle of declination of this winglet.Adopt NACASC (2) 0410 aerofoil profiles, the length of described winglet is 8%～12% wing semispan, and leading edge sweep is 40 °～50 °, the taper ratio is 0.28～0.34, top rade is 17 °～22 °, and angle of declination is 4 °～7 °, and the aerofoil profile stagger angle is-2 °～-4 °.
Beneficial effect of the present invention has:
1) lift does not significantly increase, and relatively traditional winglet has less moment of flexure to wing root, improves the structural weight income.
2) the induced drag drag-reduction effect is remarkable, thereby improves aerodynamic characteristic, improves the flight economy.
3) significantly improve the aircraft wing 1ift-drag ratio.
Description of drawings
Fig. 1 is the birds-eye view of winglet;
Fig. 2 is the left view of winglet;
Fig. 3 is the front elevation of winglet;
Fig. 4 A is the wing tip flow line plan of B wing in embodiment;
Fig. 4 B is the wing tip flow line plan of W1 wing in embodiment;
Fig. 4 C is the wing tip flow line plan of W2 wing in embodiment;
Fig. 5 A is the wing tip pressure cloud atlas of B wing in embodiment;
Fig. 5 B is the wing tip pressure cloud atlas of W1 wing in embodiment;
Fig. 5 C is the wing tip pressure cloud atlas of W2 wing in embodiment.
The specific embodiment
The present invention is described in further detail in connection with accompanying drawing and example below.
It is the birds-eye view of winglet provided by the invention as Fig. 1.A, B, C, D be four and control the erect-position aerofoil profiles, and be designated as respectively A#, B#, C#, D# aerofoil profile, wherein A# is winglet wing root aerofoil profile, and B# is the winglet aerofoil profile that has a down dip, and C# is winglet transition aerofoil profile, and D# is winglet wing tip aerofoil profile.ADEH is the winglet plane projection of shape, and AD is length, and curve A BCD is costa, and curve EFGH is the trailing edge line, and ED/AH is the taper ratio, and leading edge sweep α as shown in Figure 1.
Fig. 2 is the left view of winglet.As figure, the angle of CF and horizon CI is the stagger angle β of C# aerofoil profile, and is same, and the stagger angle of A#, B#, D# aerofoil profile is also the corresponding string of a musical instrument and horizontal angle.The note aerofoil profile is negative angle under costa partially, and upper is positive-angle partially.
Fig. 3 is the front elevation of winglet.Wherein, the angle of A# aerofoil profile and B# aerofoil profile line AB and horizon AL is the θ angle that has a down dip, and the angle between the horizon AL that mistake A is ordered and the line AD of A# aerofoil profile and D# aerofoil profile is top rade Φ.
Winglet of the present invention is by four aerofoil profile erect-position faces and leading edge and the decision of trailing edge line, and each aerofoil profile erect-position is controlled parameters with 3 respectively and controlled its space erect-position, is respectively the aerofoil profile chord length, aerofoil profile leading edge point X, Y coordinate.The important plane geometry parameter of this winglet is:
(1) length refers to winglet in the leading edge length of birds-eye view direction projection, and length is 8%～12% wing semispan.
(2) leading edge sweep refers to the angle of winglet projection leading edge in the horizontal direction and free incoming flow normal direction, and leading edge sweep is 40 °～50 °.
(3) taper ratio refers to the ratio of winglet point chord length and winglet root chord length, and the taper ratio is 0.28～0.34.
(4) top rade refers to the root string of winglet and the angle between end string plane and horizontal surface, and top rade is 17 °～22 °.
(5) stagger angle refers to the root chord line of winglet and the angle between wing wing tip root chord line, and the aerofoil profile stagger angle is-2 °～-4 °.
(6) winglet aerofoil profile refers to that winglet adopts NACA SC (2) 0410 aerofoil profiles.
(7) angle of declination refers to the angle between wing wing tip root string and bottommost aerofoil profile plane, root string place and horizontal surface, and angle of declination is 4 °～7 °.
Instantiation
Based on certain wing, add this novel cochlear winglet, design parameter is as shown in table 1, and wherein, the stagger angle of each erect-position aerofoil profile is different, and wherein B# is-4 °, and C# is-3 °, D# is-2 °.The wing that note is not added winglet is the B wing, and the wing that adds traditional fusion type winglet is the W1 wing, on the basic plane parameter of W1 wing, adds the cochlear winglet with the feature of having a down dip, and is designated as the W2 wing.Under the 0 degree angle of attack that cruises, respectively to this three width wing with CFD(Computational Fluid Dynamic) method calculates its lift coefficient Cl, drag coefficient Cd, and obtains 1ift-drag ratio K, its aeroperformance of comparative analysis, result of calculation is as shown in table 2.
The basic plane parameter of table 1 cochlear winglet
The aeroperformance result of the table 2 three slave wings
As can be seen from Table 2, under the angle of attack that cruises, with respect to the B wing, the W1 airfoil lift increases by 1.50%, and resistance descends 6.79%, and 1ift-drag ratio increases by 8.92%; The W2 airfoil lift reduces by 0.73% slightly, and resistance descends 7.10%, and 1ift-drag ratio increases by 6.64%.Installed the W2 wing of cochlear winglet additional, its lift does not increase, but slightly reduces, and therefore can not produce larger additional bending moment to the wing root; Simultaneously, have better drag-reduction effect than traditional fusion type winglet, thereby can obtain good 1ift-drag ratio income.
Can be found out by Fig. 4 A～4C, Fig. 5 A～5C, air-flow has formed very strong monomer whirlpool at B trailing edge wing tip place, and extend back and come, and in W1 and W2 wing, air-flow does not form immediately large intensity at the wing tip place and streams, and air-flow is more smooth-going, along with air-flow extends back, just form and significantly stream, intensity ratio B wing relatively a little less than, wherein the cochlear winglet is the most obvious to the dissipation in whirlpool.
Claims (8)
1. the novel cochlear fusion type winglet of a seating plane is characterized in that: on traditional fusion type winglet basis, add the feature that has a down dip, make it to become a cochlear structure; This winglet has four aerofoil profile occupy-place faces to control, and forms the winglet front and rear edge, is designated as respectively A#, B#, C#, D# aerofoil profile, and wherein A# is winglet wing root aerofoil profile, and B# is the winglet aerofoil profile that has a down dip, and C# is winglet transition aerofoil profile, and D# is winglet wing tip aerofoil profile; The B# aerofoil profile that has a down dip is controlled the size of the angle of declination of this winglet.
2. the novel cochlear fusion type winglet of a kind of seating plane according to claim 1, it is characterized in that: the length of described winglet is 8%～12% wing semispan.
3. the novel cochlear fusion type winglet of a kind of seating plane according to claim 1, it is characterized in that: the leading edge sweep of described winglet is 40 °～50 °.
4. the novel cochlear fusion type winglet of a kind of seating plane according to claim 1, it is characterized in that: the taper ratio of described winglet is 0.28～0.34.
5. the novel cochlear fusion type winglet of a kind of seating plane according to claim 1, it is characterized in that: the top rade of described winglet is 17 °～22 °.
6. the novel cochlear fusion type winglet of a kind of seating plane according to claim 1, it is characterized in that: the angle of declination of described winglet is 4 °～7 °.
7. the novel cochlear fusion type winglet of a kind of seating plane according to claim 1, it is characterized in that: the aerofoil profile stagger angle of described winglet is-2 °～-4 °.
8. the novel cochlear fusion type winglet of a kind of seating plane according to claim 1, it is characterized in that: the length 3m of described winglet, 50 ° of leading edge sweeps, taper is than 0.32,20 ° of top rades, 5 ° of angle of declinations, the stagger angle of each occupy-place aerofoil profile is different, wherein B# is-4 °, and C# is-3 °, and D# is-2 °.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220590766 CN202953169U (en) | 2012-11-09 | 2012-11-09 | Novel spoon-shaped blended winglet for civil airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220590766 CN202953169U (en) | 2012-11-09 | 2012-11-09 | Novel spoon-shaped blended winglet for civil airplane |
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| CN202953169U true CN202953169U (en) | 2013-05-29 |
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| CN 201220590766 Expired - Fee Related CN202953169U (en) | 2012-11-09 | 2012-11-09 | Novel spoon-shaped blended winglet for civil airplane |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108974326A (en) * | 2018-06-28 | 2018-12-11 | 西安交通大学 | A kind of bionical wave leading edge winglet device |
| CN112224383A (en) * | 2020-09-21 | 2021-01-15 | 中电科芜湖通用航空产业技术研究院有限公司 | Micro-down-trans-form wingtip winglet keeping transverse static stability of wing unchanged and wing |
| CN112298526A (en) * | 2020-10-14 | 2021-02-02 | 汕头大学 | Wingtip winglet structure and aircraft |
| CN112478127A (en) * | 2020-12-04 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Flying wing unmanned aerial vehicle with geometry twists reverse structure |
| CN113306698A (en) * | 2021-06-16 | 2021-08-27 | 西安交通大学 | Double-feather wingtip winglet device with variable inclination angle |
-
2012
- 2012-11-09 CN CN 201220590766 patent/CN202953169U/en not_active Expired - Fee Related
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108974326A (en) * | 2018-06-28 | 2018-12-11 | 西安交通大学 | A kind of bionical wave leading edge winglet device |
| CN112224383A (en) * | 2020-09-21 | 2021-01-15 | 中电科芜湖通用航空产业技术研究院有限公司 | Micro-down-trans-form wingtip winglet keeping transverse static stability of wing unchanged and wing |
| CN112298526A (en) * | 2020-10-14 | 2021-02-02 | 汕头大学 | Wingtip winglet structure and aircraft |
| CN112478127A (en) * | 2020-12-04 | 2021-03-12 | 中国航空工业集团公司沈阳飞机设计研究所 | Flying wing unmanned aerial vehicle with geometry twists reverse structure |
| CN113306698A (en) * | 2021-06-16 | 2021-08-27 | 西安交通大学 | Double-feather wingtip winglet device with variable inclination angle |
| CN113306698B (en) * | 2021-06-16 | 2023-07-04 | 西安交通大学 | Double-feather type wing tip winglet device with variable inclination angle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C53 | Correction of patent for invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Kong Bo Inventor after: Liu Ming Inventor after: Wu Tiefeng Inventor after: Han Xiaoyong Inventor after: Tian Yun Inventor after: Liu Peiqing Inventor before: Kong Bo Inventor before: Tian Yun Inventor before: Liu Peiqing |
|
| COR | Change of bibliographic data |
Free format text: CORRECT: INVENTOR; FROM: KONG BO TIAN YUN LIU PEIQING TO: KONG BO LIU MING WU TIEFENG HAN XIAOYONG TIAN YUN LIU PEIQING |
|
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20130529 Termination date: 20131109 |