CN106240797A - A kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics - Google Patents
A kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics Download PDFInfo
- Publication number
- CN106240797A CN106240797A CN201610808423.5A CN201610808423A CN106240797A CN 106240797 A CN106240797 A CN 106240797A CN 201610808423 A CN201610808423 A CN 201610808423A CN 106240797 A CN106240797 A CN 106240797A
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- wing
- leading edge
- sawtooth
- vortex generator
- avertence
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
-
- 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
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
- B64C2003/146—Aerofoil profile comprising leading edges of particular shape
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Toys (AREA)
Abstract
nullA kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics，Including Inside Leading Edge Flaps、Outboard Leading Edge Flap、Outer wing、Aileron and inner wing，The outside of inner wing and the fixing connection of outer wing，Outboard Leading Edge Flap is connected to outer nose of wing，Inside Leading Edge Flaps is connected to interior nose of wing，The trailing edge of outer wing connects aileron，Also include left avertence vortex generator and right avertence vortex generator，Described left avertence vortex generator and right avertence vortex generator are connected with outer wing upper surface，For formula obtuse sawtooth transition of splaying between described Inside Leading Edge Flaps and Outboard Leading Edge Flap，This obtuse sawtooth transition link together with Outboard Leading Edge Flap Tong Bu deflection，The vortex generator of 2 reverse-biased types is installed at the formula of splaying blunt type sawtooth downstream direction lower edge，Its longitudinal Vortex produced introduces energy injection to the low-yield air-flow in sawtooth whirlpool from freely flowing，Strengthen the ability of the adverse pressure gradient that air-flow overcomes shock wave to cause，Air-flow is delayed to separate.
Description
Technical field
The present invention relates to a kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics.
Background technology
Aircraft flow field in transonic speed maneuvering flight is sufficiently complex, and particularly vortex and the interaction of shock wave are to vortex
The impact ruptured and separate generation is bigger.With the swept-wing layout aircraft of leading edge dog-tooth when transonic speed maneuvering flight, shock wave
The eddy current that can cause leading edge of a wing sawtooth ruptures, and then causes air-flow to separate.If the shock wave formed on the wing of left and right is asymmetric, then
Cause separating flowing field the most asymmetric, thus form rolling moment so that fall off side wing absence of aura, cause induction
" wing undershoot " phenomenon occurs, and the lateral stability of aircraft and maneuverability will be remarkably decreased, and greatly threaten flight safety.How to exist
On the premise of ensureing aircraft lifting resistance characteristic and stealth effect, improve the transonic speed machine of this type of band sawtooth swept-wing layout aircraft
Dynamic characteristic, has important engineer applied and is worth.
Summary of the invention
For disadvantage mentioned above, the present invention provides a kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics.
It is an object of the invention to be achieved through the following technical solutions:
A kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics, including Inside Leading Edge Flaps, the outside leading edge flap
The wing, outer wing, aileron and inner wing, the outside of inner wing and outer wing are fixing to be connected, and Outboard Leading Edge Flap is connected to outer nose of wing, before inner side
Edge wing flap is connected to interior nose of wing, and the trailing edge of outer wing connects aileron, also includes that left avertence vortex generator and right avertence eddy current occur
Device, described left avertence vortex generator and right avertence vortex generator be connected with outer wing upper surface, described Inside Leading Edge Flaps and
For formula obtuse sawtooth transition of splaying between Outboard Leading Edge Flap, this obtuse sawtooth transition and Outboard Leading Edge Flap link together same
Step deflection, has a slit, before described obtuse sawtooth transition between Inside Leading Edge Flaps and described obtuse sawtooth transition
Edge with come flow path direction in wingpiston in an acute angle.
The present invention also has a following technical characteristic:
The leading edge of 1, described obtuse sawtooth transition is 15 °～75 ° with carrying out flow path direction angular range in wingpiston.
2, described left avertence vortex generator and right avertence vortex generator setting angle scope are left avertence 30 °～right avertence 30 °.
3, described left avertence vortex generator and right avertence vortex generator are near obtuse sawtooth transition.
The invention have the benefit that formation is splayed by redesigning the Outboard Leading Edge Flap sawtooth of swept-back wing
Formula blunt type sawtooth, can weaken or eliminate the eddy current that sawtooth is deviate from top airfoil.Strength of vortex near sawtooth reduces, top airfoil
Flowing more stable, eddy current can be reduced under Shock wave interaction, rupture the air-flow separating ranges of formation, contribute to improving wing and dash forward
So stalling characteristics, install the vortex generator of 2 reverse-biased types at the formula of splaying blunt type sawtooth downstream direction lower edge, and it is vertical that it produces
To whirlpool from freely flowing introducing energy injection to the low-yield air-flow in sawtooth whirlpool, strengthen the adverse pressure gradient that air-flow overcomes shock wave to cause
Ability, delay air-flow to separate, on the basis of the formula of splaying blunt type sawtooth, improve upper surface of the airfoil stalling characteristic further, improvement flies
Machine is aerodynamic characteristic and buffeting characteristic in transonic speed maneuvering flight.The present invention designs simply, it is reasonable, with low cost, flexible to construct
Practicality, has preferable application prospect.
Accompanying drawing explanation
Fig. 1 is the overall structure top view of the present invention.
Fig. 2 is partially schematic Fig. 1 of the present invention.
Fig. 3 is the A-A profile of Fig. 2.
Fig. 4 is partially schematic Fig. 2 of the present invention.
Fig. 5 is partially schematic Fig. 3 of the present invention.
Fig. 6 is the overall structure figure of the present invention.
Detailed description of the invention
The invention will be further described in citing below in conjunction with the accompanying drawings:
Embodiment 1
As shown in Figure 1: a kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics, including Inside Leading Edge Flaps 1,
Outboard Leading Edge Flap 4, outer wing 5, aileron 6 and inner wing 7, the outside of inner wing 7 and the fixing connection of outer wing 5, Outboard Leading Edge Flap 4 connects
In outer wing 5 leading edge, Inside Leading Edge Flaps 1 is connected to inner wing 7 leading edge, and the trailing edge of outer wing 5 connects aileron 6, also includes left avertence whirlpool
Flow-generator 8 and right avertence vortex generator 9, described left avertence vortex generator 8 and right avertence vortex generator 9 and table on outer wing 5
Face connects, for formula obtuse sawtooth transition 3 of splaying, this obtuse sawtooth between described Inside Leading Edge Flaps 1 and Outboard Leading Edge Flap 4
Transition 3 link together with Outboard Leading Edge Flap Tong Bu deflection, between Inside Leading Edge Flaps 1 and described obtuse sawtooth transition 3
Have a slit, the leading edge of described obtuse sawtooth transition 3 with come flow path direction in wingpiston in an acute angle.Described obtuse
The leading edge of sawtooth transition 3 is 15 °～75 ° with carrying out flow path direction angular range in wingpiston.Described left avertence eddy current occurs
Device 8 and right avertence vortex generator 9 setting angle scope are left avertence 30 °～right avertence 30 °.Described left avertence vortex generator 8 and the right side
Vortex generator 9 partially is near obtuse sawtooth transition 3.The present embodiment during transonic speed is motor-driven, Inside Leading Edge Flaps 1, outside
The deflection angle of droope snoot 4 and aileron 6 is determined by control program of flying according to state of flight.
Embodiment 2
As shown in figures 2-6: a kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics, including Inside Leading Edge Flaps
1, Outboard Leading Edge Flap 4, outer wing 5, aileron 6 and inner wing 7, the outside of inner wing 7 and the fixing connection of outer wing 5, Outboard Leading Edge Flap 4 is even
Being connected on outer wing 5 leading edge, Inside Leading Edge Flaps 1 is connected to inner wing 7 leading edge, and the trailing edge of outer wing 5 connects aileron 6, also includes left avertence
Vortex generator 8 and right avertence vortex generator 9, described left avertence vortex generator 8 and right avertence vortex generator 9 with on outer wing 5
Surface connects, and for formula obtuse sawtooth transition 3 of splaying between described Inside Leading Edge Flaps 1 and Outboard Leading Edge Flap 4, this obtuse is sawed
Tooth transition 3 links together with Outboard Leading Edge Flap Tong Bu deflection, Inside Leading Edge Flaps 1 and described obtuse sawtooth transition 3 it
Between have a slit, the leading edge of described obtuse sawtooth transition 3 with come flow path direction in wingpiston in an acute angle.A described left side
Vortex generator 8 and right avertence vortex generator 9 are near obtuse sawtooth transition 3 partially.The wing aspect ratio of the present embodiment is 2.0, interior
Side droope snoot 1 leading edge sweep 30 °, Outboard Leading Edge Flap 4 leading edge sweep 35 °, Inside Leading Edge Flaps 1 and the outside leading edge flap
Inclined 10 ° of the wing 4 times, inclined 5 ° of aileron 6 times.Formula of wherein splaying blunt type sawtooth 3 leading edge with carrying out flow path direction in wingpiston within angle is
30°.Can weaken or eliminate the separation whirlpool near sawtooth 3.Install below the formula of splaying blunt type sawtooth 32 equivalently-sized anti-
Bias tyre vortex generator.Left avertence vortex generator 8 height h is 0.012m, and length l is 0.057m, and thickness d is 0.0015m, left avertence
Vortex generator 8 front end hypotenuse inclination alpha is 20 °, and front end, rear end hypotenuse angle of inclination beta is 45 °, and (vortex generator is the most flat for established angle
The angle that face and dead ahead flow) it is left avertence 4 °, forward terminal distance front part of a Chinese robe or jacket hinge lines distance D1For 0.124m.Right avertence eddy current occurs
Device 9 physical dimension is all identical with left avertence vortex generator 8, and established angle is right avertence 27 °, forward terminal distance front part of a Chinese robe or jacket hinge lines distance D2
For 0.127m.Vortex generator of the present invention can delay air-flow to separate, and in transonic speed maneuvering flight, improves further
Band splay formula sawtooth swept-back wing aircraft transonic speed aerodynamic characteristic and buffet characteristic, obtain in the wind tunnel test of model aircraft
Checking.
Claims (4)
1. improve a wing for band sawtooth swept-back wing transonic speed maneuvering characteristics, including Inside Leading Edge Flaps (1), the outside leading edge flap
The wing (4), outer wing (5), aileron (6) and inner wing (7), the outside of inner wing (7) and outer wing (5) are fixing to be connected, Outboard Leading Edge Flap (4)
Being connected to outer wing (5) leading edge, Inside Leading Edge Flaps (1) is connected to inner wing (7) leading edge, and the trailing edge of outer wing (5) connects aileron
(6), it is characterised in that: also include that left avertence vortex generator (8) and right avertence vortex generator (9), described left avertence eddy current occur
Device (8) and right avertence vortex generator (9) are connected with outer wing (5) upper surface, described Inside Leading Edge Flaps (1) and the outside leading edge flap
For formula obtuse sawtooth transition (3) of splaying between the wing (4), this obtuse sawtooth transition (3) and Outboard Leading Edge Flap link together same
Step deflection, has a slit, described obtuse sawtooth mistake between Inside Leading Edge Flaps (1) and described obtuse sawtooth transition (3)
Cross the leading edge of (3) with come flow path direction in wingpiston in an acute angle.
A kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics the most according to claim 1, it is characterised in that:
The leading edge of described obtuse sawtooth transition (3) is 15 °-75 ° with carrying out flow path direction angular range in wingpiston.
A kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics the most according to claim 1, it is characterised in that:
Described left avertence vortex generator (8) and right avertence vortex generator (9) setting angle scope are 30 °-right avertence of left avertence 30 °.
A kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics the most according to claim 1, it is characterised in that:
Described left avertence vortex generator (8) and right avertence vortex generator (9) are near obtuse sawtooth transition (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610808423.5A CN106240797A (en) | 2016-09-07 | 2016-09-07 | A kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610808423.5A CN106240797A (en) | 2016-09-07 | 2016-09-07 | A kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics |
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| CN106240797A true CN106240797A (en) | 2016-12-21 |
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|---|---|---|---|
| CN201610808423.5A Pending CN106240797A (en) | 2016-09-07 | 2016-09-07 | A kind of wing improving band sawtooth swept-back wing transonic speed maneuvering characteristics |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110697022A (en) * | 2019-10-11 | 2020-01-17 | 中国航空工业集团公司西安飞机设计研究所 | Propeller aircraft wing and propeller aircraft |
| CN117755478A (en) * | 2024-02-22 | 2024-03-26 | 中国航空工业集团公司西安飞机设计研究所 | Pneumatic layout structure of airplane and operation method thereof |
Citations (5)
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|---|---|---|---|---|
| US6513754B1 (en) * | 2001-09-26 | 2003-02-04 | The United States Of America As Represented By The Secretary Of The Navy | Transonic flow shockwave position stabilizer |
| CN103057691A (en) * | 2011-09-06 | 2013-04-24 | 空中客车西班牙运营有限责任公司 | Aircraft tail surface with leading edge section of undulated shape |
| CN103592099A (en) * | 2013-11-28 | 2014-02-19 | 中国航空工业集团公司沈阳空气动力研究所 | Measuring equipment for wind tunnel free-rolling vibration test and measuring method thereof |
| CN105644770A (en) * | 2015-12-30 | 2016-06-08 | 哈尔滨工业大学 | Sharkskin-imitating resistance-reducing wing |
| CN205998113U (en) * | 2016-09-07 | 2017-03-08 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of wing with sawtooth swept-back wing transonic speed maneuvering characteristics for improvement |
-
2016
- 2016-09-07 CN CN201610808423.5A patent/CN106240797A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6513754B1 (en) * | 2001-09-26 | 2003-02-04 | The United States Of America As Represented By The Secretary Of The Navy | Transonic flow shockwave position stabilizer |
| CN103057691A (en) * | 2011-09-06 | 2013-04-24 | 空中客车西班牙运营有限责任公司 | Aircraft tail surface with leading edge section of undulated shape |
| CN103592099A (en) * | 2013-11-28 | 2014-02-19 | 中国航空工业集团公司沈阳空气动力研究所 | Measuring equipment for wind tunnel free-rolling vibration test and measuring method thereof |
| CN105644770A (en) * | 2015-12-30 | 2016-06-08 | 哈尔滨工业大学 | Sharkskin-imitating resistance-reducing wing |
| CN205998113U (en) * | 2016-09-07 | 2017-03-08 | 中国航空工业集团公司哈尔滨空气动力研究所 | A kind of wing with sawtooth swept-back wing transonic speed maneuvering characteristics for improvement |
Non-Patent Citations (1)
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|---|
| 钱锟: "F/A-18E/F机翼突然失速问题的调查经过和解决方案", 《国际航空杂志》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110697022A (en) * | 2019-10-11 | 2020-01-17 | 中国航空工业集团公司西安飞机设计研究所 | Propeller aircraft wing and propeller aircraft |
| CN117755478A (en) * | 2024-02-22 | 2024-03-26 | 中国航空工业集团公司西安飞机设计研究所 | Pneumatic layout structure of airplane and operation method thereof |
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Application publication date: 20161221 |
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