CN109131833A - A kind of high aspect ratio wing of high lift-rising - Google Patents
A kind of high aspect ratio wing of high lift-rising Download PDFInfo
- Publication number
- CN109131833A CN109131833A CN201811134992.1A CN201811134992A CN109131833A CN 109131833 A CN109131833 A CN 109131833A CN 201811134992 A CN201811134992 A CN 201811134992A CN 109131833 A CN109131833 A CN 109131833A
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- wing
- flap
- lift
- aspect ratio
- wing flap
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- 238000013461 design Methods 0.000 abstract description 17
- 230000000694 effects Effects 0.000 abstract description 10
- 238000000034 method Methods 0.000 description 8
- 238000010586 diagram Methods 0.000 description 3
- 238000000926 separation method Methods 0.000 description 3
- 230000002411 adverse Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000012790 confirmation Methods 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000011156 evaluation Methods 0.000 description 1
- 239000012530 fluid Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/36—Structures adapted to reduce effects of aerodynamic or other external heating
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C9/00—Adjustable control surfaces or members, e.g. rudders
- B64C9/14—Adjustable control surfaces or members, e.g. rudders forming slots
- B64C9/16—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing
- B64C9/20—Adjustable control surfaces or members, e.g. rudders forming slots at the rear of the wing by multiple flaps
Abstract
The application belongs to aircraft aerodynamic arrangement design field more particularly to a kind of high aspect ratio wing of high lift-rising.It is made of main wing 1 and wing flap 2.By the design to flap gap parameter Gap, seam lap-joint Over-lap, the high lift-rising effect of high aspect ratio wing is realized, guarantee that there is good takeoff and landing performance and landing safety while high cruise performance.The application is simple and easy, and wing flap is deflected to simple deflection mechanism, does not need complicated wing flap withdrawing mechanism, can reduce the complexity and reliability of system.
Description
Technical field
The application belongs to aircraft aerodynamic arrangement design field more particularly to a kind of high aspect ratio wing of high lift-rising.
Background technique
The design of aircraft wing aerodynamic arrangement must combine high low-speed performance, and often exist therebetween conflicting
Relationship.In high-performance cruise, it is desirable that wing area is as small as possible, and aspect ratio is as big as possible, to reduce wing aerodynamic resistance, improves
Cruise lift resistance ratio, and then promotes voyage and endurance, improves cruise performance, however since structural strength etc. limits, wingspan length is not
May be infinitely great, therefore when wingspan length can not increase, the increase of aspect ratio can only be realized by reducing wing chord length, this
It will cause the reduction of wing area；In the low speed landing stage, it is desirable that wing area is as big as possible, to increase lower-speed state lift
System reduces speed of departing, reduces landing speed, reduces distance of landing run, reduce the probability that aircraft guns off the runway, promoted
Landing safety.Therefore, in wing design, contradiction between height is solved, it is necessary to which design can increase low speed on wing
The movable rudder face of landing stage lift, i.e. lift-increasing flap.Traditional camber flap is to increase lift by increasing wing camber
The purpose of coefficient, however be easy to separate from the side for generating suction due to flowing, tail is simultaneously unstable, the flap under middle isogonic
With regard to separating on the wing, so bring lift increase is not considerable.And single slotted flap can be set by reasonable seam parameter
Meter improves the flow field quality between seam, improves the boundary layer conditions on aerofoil by seam jet stream, and then enhance boundary layer
The ability of adverse pressure gradient is born, to delay to separate, realizes the purpose that available lift is significantly increased.
Separately having Chinese patent notification number is CN106542081A, and a kind of wing flap design is disclosed on March 29th, 2017.
A kind of single seam fowler formula wing flap design of (1) -0313 aerofoil profile of NASA MS, the wing flap chord length account for the 29% of the total chord length of aerofoil profile, the i.e. flap
The wing is by 71% position of aerofoil profile chord length, until airfoil trailing edge；The relative radius on wing flap section head is 0.7%, and wing flap cuts open
The relative thickness in face is 7%；The wing flap cabin of the wing flap extends to always wing flap chord length since 71% position of aerofoil profile string
96% position, therefore aerofoil profile upper surface is actually to be overlapped with flap upper surface from aerofoil profile chord length 96% to 100%；With calculating
In main plane and the flap when wing flap expansion of fluid dynamics techniques (CFD) numerical simulation calculation NASA MS (1) -0313 aerofoil profile
Air-flow mobility status on the wing, calculated result show that the air-flow of main plane lower surface can actually accelerate to flow through wing flap and main plane
Between gap, and be directly injected in flap upper surface with higher speed.The seam of above-mentioned patent is designed for wing flap
The effect is unsatisfactory for lift-rising.
Summary of the invention
In order to overcome the drawbacks of the prior art, this application provides a kind of high aspect ratio wing of high lift-rising, the purpose is to
Reach the safety for improving lift in the takeoff and landing stage, promoting landing.
In order to solve the above-mentioned technical problem, the application the technical solution adopted is that:
A kind of high aspect ratio wing of high lift-rising, including main wing and wing flap, it is characterised in that: the line of demarcation of the wing flap and main wing
It is formed by connecting by 3 points of burble point A, B, C with curve；The burble point A be upper surface of the airfoil wing flap and main wing burble point,
Burble point A is 0.81 times of local chord, and the burble point C is the wing flap of wing lower surface and the burble point of main wing, and burble point C is
0.736 times of local chord, burble point B are wing flap leading edge point, and burble point B is 0.71 times of local chord.The local chord is
When wing flap does not deflect, some opened up along wing put to the end to section First Point apart from (see figure 1).
Deflection angle of the wing flap 2 in takeoff and landing is 10 °~40 °, preferably 30 °.
Flap gap width after the wing flap deflection is 0.005~0.03 times of local chord, preferably 0.01 times of locality
Chord length.
The amount of lap of the flap gap is.0.02~0.07 times of local chord, preferably 0.06 times of local chord.
The application has the following advantages:
The lift in takeoff and landing stage can be significantly increased in the trailing edge single slotted flap design of the application, reduce take-off and landing
Speed reduces distance of landing run, reduces the probability for flying to gun off the runway, and promotes landing safety.
Detailed description of the invention
Fig. 1 is wing flap shape and deflection design diagram；
Fig. 2 is influence curve figure of the seam width to lift-rising effect；
Fig. 3 is influence curve figure of the seam amount of lap to lift-rising effect；
Fig. 4 is two sections of single slotted flap schematic diagrames inside and outside high aspect ratio wing rear；
Fig. 5 is different wing flap lift-rising effect contrast figures (results of wind tunnel).
Marked in the figure: 1, main wing, 2, wing flap, 3, local chord, 4, wing rear spar, 5, main wing envelope edge strip.
Specific embodiment
The application is further elaborated with reference to the accompanying drawing, but the application is not limited to following embodiment, the method
It is unless otherwise instructed conventional method, the material can be gotten from open business unless otherwise instructed.
Whether process one: marking on wing structure back rest 4(figure, with) it is 0.69 times of local chord 3, wing flap, which must not design, to be surpassed
The wing structure back rest 4 out, in the burble point A of 3 Position Design wing flap and main wing of 0.81 times of local chord of upper surface of the airfoil, in wing
The burble point C of 0.736 times of lower surface local chord 3 Position Design wing flap and main wing, selects point B appropriate before burble point,
0.71 times of local chord 3 is wing flap leading edge point, and spline curve is used to connect 3 points of A, B, C lines of demarcation as wing flap 2 and main wing 1,
Designing 2 deflection angle of wing flap is 30 °, is specifically shown in Fig. 1；
Process two: flap gap width design.Seam width indication is shown in Fig. 1.Based on dimensional airfoil, seam amount of lap is kept
Over-lap is that 0.015 times of local chord 3 is constant, using CFD means, is carried out to the lift that wing flap under different seam width generates
Analysis is calculated, calculating state is α=6 °, Ma=0.2, Re=4.66 × 106, as a result see Fig. 2, see from figure, increase with seam width
Add, lift coefficient first increases and reduces afterwards, and when Gap is 0.01 times of local chord 3, lift coefficient reaches maximum, shows wing flap at this time
Seam amount of jet is most strong, and to improving, flow separation effect is most significant, and therefore, selection 0.01 times of local chord 3 of seam width is the flap
The best seam width of the wing；
Process three: flap gap amount of lap design.Seam amount of lap schematic diagram is shown in Fig. 1.Based on dimensional airfoil, seam is kept
Width G ap is that 0.016 times of local chord 3 is constant, using CFD means, lift that wing flap under different seam amounts of lap is generated into
Row calculates analysis, and calculating state is α=6 °, Ma=0.2, Re=4.66 × 106, as a result see Fig. 3, see from figure, as seam is taken
The amount of connecing increases, and lift coefficient presentation first increases the trend reduced afterwards, reaches most when Over-lap is 0.06 times of local chord 3
Greatly, show that the jet stream of wing flap at this time and main wing reaches best match state, there is the jet stream of sufficient intensity to produce effectively separation
Control, and the energy of flow in main plane boundary layer is increased, therefore, selection 0.06 times of local chord 3 of seam amount of lap is the flap
The best seam amount of lap of the wing；
Process four: designing inside and outside two sections of wing flaps on the high aspect ratio wing that half length is 8.9 meters, and flap gap width is 0.01
Times local chord 3, seam amount of lap are 0.06 times of local chord 3.Final wing flap design parameter is as follows:
Inner segment wing flap length is 1.228 meters, and wing flap is opened up to most inner side apart from 1.01 meters of the aircraft plane of symmetry, and wing flap root is apart from wing
The reserved 0.3 meter of space of wing root is that inner segment wing flap installs steering engine consideration, and 1.87 meters of wing flap wing root wing chord length, wing flap chord length are
0.494 meter, seam width be 18.7 millimeters, seam amount of lap is 112.2 millimeters, wing flap wingtip airfoil chord is 1.088 meters a length of, the flap
Wing chord is 0.287 meter a length of, seam width is 10.88 millimeters, seam amount of lap is 65.28 millimeters, and angle of flap deflection degree is 30 °,
It is specifically shown in Fig. 4.
Outer segment wing flap length is 1.5575 meters, and wing flap root is outer apart from the reserved 0.115 meter of space of inner segment wing flap wingtip
Section wing flap installation steering engine considers that wing flap wing root airfoil chord is 1.043 meters a length of, wing flap chord length is 0.274 meter, seam width is
10.43 millimeters, seam amount of lap be 62.58 millimeters, wing flap wingtip airfoil chord is 0.9 meter a length of, wing flap chord length is 0.2376 meter, seam
Road width is 9 millimeters, seam amount of lap is 54 millimeters, and angle of flap deflection degree is 30 °, is specifically shown in Fig. 4.
Process five: design processing model in wind tunnel simultaneously carries out wind tunnel test verifying and confirmation to its lift-rising effect, sees figure
5.To see from figure, compared with full machine lift coefficient when no wing flap, camber flap lift coefficient only increases by 0.25 or so, and
It is separated in High Angle of Attack, lift-rising effect decreases, and single slotted flap lift coefficient described herein increases up to 0.5 left side
The right side is twice compared with lift-rising effect caused by camber flap, simultaneously as seam jet stream improves the separation of wing flap and main wing,
Therefore single slotted flap described herein is still fine in the small lift-rising effect of High Angle of Attack.
By quality and Performance Evaluation, trailing edge single slotted flap designed by the application can make to take off liftoff speed
Degree reduces 35km/h, and rotation speed of taking off reduces 27km/h, and landing speed reduces 31km/h, and distance of landing run reduces
The performance and landing safety in landing stage greatly improved in 220m.
Claims (4)
1. a kind of high aspect ratio wing of high lift-rising, including main wing (1) and wing flap (2), it is characterised in that: the wing flap (2) with
The line of demarcation of main wing (1) is formed by connecting by 3 points of burble point A, B, C with curve；The burble point A is the wing flap of upper surface of the airfoil
(2) with the burble point of main wing (1), burble point A is 0.81 times of local chord (3), and the burble point C is the wing flap of wing lower surface
(2) with the burble point of main wing envelope edge strip (5), burble point C is 0.736 times of local chord (3), and burble point B is wing flap leading edge point, point
It is 0.71 times of local chord (3) from point B.
2. a kind of high aspect ratio wing of high lift-rising according to claim 1, it is characterised in that: the wing flap (2) exists
Deflection angle when takeoff and landing is 10 °~40 °.
3. a kind of high aspect ratio wing of high lift-rising according to claim 1, it is characterised in that: wing flap (2) deflection
Flap gap width afterwards is 0.005~0.03 times of local chord (3).
4. a kind of high aspect ratio wing of high lift-rising according to claim 1, it is characterised in that: the flap gap is taken
The amount of connecing is 0.02~0.07 times of local chord (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811134992.1A CN109131833A (en) | 2018-09-28 | 2018-09-28 | A kind of high aspect ratio wing of high lift-rising |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811134992.1A CN109131833A (en) | 2018-09-28 | 2018-09-28 | A kind of high aspect ratio wing of high lift-rising |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109131833A true CN109131833A (en) | 2019-01-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811134992.1A Pending CN109131833A (en) | 2018-09-28 | 2018-09-28 | A kind of high aspect ratio wing of high lift-rising |
Country Status (1)
| Country | Link |
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| CN (1) | CN109131833A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111498085A (en) * | 2020-04-15 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | High-altitude long-endurance unmanned aerial vehicle wing suitable for lower single-wing layout |
| CN112339987A (en) * | 2020-10-29 | 2021-02-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Double-slit flap with flap fixedly connected with additional wing |
| CN113212733A (en) * | 2021-04-30 | 2021-08-06 | 成都飞机工业（集团）有限责任公司 | Large-aspect-ratio conventional-layout unmanned aerial vehicle gust load alleviation method |
| CN113704886A (en) * | 2021-08-16 | 2021-11-26 | 成都飞机工业（集团）有限责任公司 | Rapid and preferred seam channel airfoil design method |
| CN115027663A (en) * | 2022-08-10 | 2022-09-09 | 中国空气动力研究与发展中心计算空气动力研究所 | Wing fusion control method realized through jet flow |
| CN115520405A (en) * | 2022-11-29 | 2022-12-27 | 四川腾盾科技有限公司 | Design method and structure of trailing edge fullerene flap sliding device |
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| CN106800086A (en) * | 2015-11-26 | 2017-06-06 | 哈尔滨飞机工业集团有限责任公司 | The single seam fowler formula wing flap design of one kind of the aerofoil profiles of NASA MS (1) -0317 |
| CN209008845U (en) * | 2018-09-28 | 2019-06-21 | 成都飞机工业（集团）有限责任公司 | A kind of high aspect ratio wing of high lift-rising |
| CN115783242A (en) * | 2022-12-16 | 2023-03-14 | 江西洪都航空工业集团有限责任公司 | High lift device with guide vane type double-slit flap |
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2018
- 2018-09-28 CN CN201811134992.1A patent/CN109131833A/en active Pending
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| CN101323371A (en) * | 2008-06-24 | 2008-12-17 | 北京航空航天大学 | Lift augmenter with united jet flow structure on wing flap |
| CN202320772U (en) * | 2011-09-02 | 2012-07-11 | 北京航空航天大学 | High lift device of double-aisle large-type passenger plane |
| CN102642615A (en) * | 2012-05-11 | 2012-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Airplane high lift device with single slotted flaps |
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| CN209008845U (en) * | 2018-09-28 | 2019-06-21 | 成都飞机工业（集团）有限责任公司 | A kind of high aspect ratio wing of high lift-rising |
| CN115783242A (en) * | 2022-12-16 | 2023-03-14 | 江西洪都航空工业集团有限责任公司 | High lift device with guide vane type double-slit flap |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111498085A (en) * | 2020-04-15 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | High-altitude long-endurance unmanned aerial vehicle wing suitable for lower single-wing layout |
| CN112339987A (en) * | 2020-10-29 | 2021-02-09 | 中电科芜湖通用航空产业技术研究院有限公司 | Double-slit flap with flap fixedly connected with additional wing |
| CN113212733A (en) * | 2021-04-30 | 2021-08-06 | 成都飞机工业（集团）有限责任公司 | Large-aspect-ratio conventional-layout unmanned aerial vehicle gust load alleviation method |
| CN113704886A (en) * | 2021-08-16 | 2021-11-26 | 成都飞机工业（集团）有限责任公司 | Rapid and preferred seam channel airfoil design method |
| CN113704886B (en) * | 2021-08-16 | 2023-10-03 | 成都飞机工业（集团）有限责任公司 | Rapid and preferential design method for seam airfoil |
| CN115027663A (en) * | 2022-08-10 | 2022-09-09 | 中国空气动力研究与发展中心计算空气动力研究所 | Wing fusion control method realized through jet flow |
| CN115027663B (en) * | 2022-08-10 | 2022-11-22 | 中国空气动力研究与发展中心计算空气动力研究所 | Wing fusion control method realized through jet flow |
| CN115520405A (en) * | 2022-11-29 | 2022-12-27 | 四川腾盾科技有限公司 | Design method and structure of trailing edge fullerene flap sliding device |
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Application publication date: 20190104 |
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