CN109665090A - A kind of circulation control deformation wing flap for supersonic wing - Google Patents
A kind of circulation control deformation wing flap for supersonic wing Download PDFInfo
- Publication number
- CN109665090A CN109665090A CN201910079375.4A CN201910079375A CN109665090A CN 109665090 A CN109665090 A CN 109665090A CN 201910079375 A CN201910079375 A CN 201910079375A CN 109665090 A CN109665090 A CN 109665090A
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- China
- Prior art keywords
- wing
- wing flap
- supersonic
- flap
- circulation control
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
- B64C3/50—Varying camber by leading or trailing edge flaps
-
- 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
Abstract
The invention discloses a kind of circulation controls for supersonic wing to deform wing flap, the air blowing that the deformation wing flap upper end is equipped with strip is stitched, it needs to increase high-lift leading-edge device simultaneously, to reduce up-front air-flow separation, under lower-speed state, deformation wing flap bends to crescent, seam of blowing simultaneously blows out high-speed jet layer, due to the presence of Coanda effect, jet layer is close to curved surface flowing, it deflects along curved surface, finally oliquely downward blow out, the wing flap of crescent is equivalent to the arc-shaped rear of circulation control technology at this time, this process considerably increases the circular rector of wing, improve lift coefficient, simultaneously under cruising condition, wing flap keeps straightened condition, it not will increase additional friction, the configuration of the present invention is simple, it does not need to increase wing thickness, suitable for supersonic speed thin airfoil, liter of the supersonic wing under lower-speed state can be greatly improved Force coefficient.
Description
Technical field
The present invention relates to supersonic vehicle pneumatic design fields, and in particular to a kind of circular rector control for supersonic wing
System deformation wing flap.
Background technique
Supersonic wing is in the prior art in order to reduce wave resistance, generally uses thin airfoil, and the low-speed performance of thin airfoil compared with
Difference needs to open high lift device when the takeoff and anding stage, speed was lower to increase lift, while using the biggish angle of attack.
Common high lift device is usually mechanical wing flap on aircraft wing at present, is stretched out in the leading edge or rear of wing
Or deflection control plane increases wing area, and then improve the lift coefficient of wing, on airliner to increase wing camber
The typical wing flap used is slotted flap, and multistage aerofoil is unfolded at wing rear in this wing flap, there are gap between each aerofoil,
The higher air-flow of wing following pressure flow to the upper surface of every section of wing flap by gap, is that the boundary-layer of upper surface supplements energy
Amount, is not easily separate upper surface air-flow.
In addition to mechanical wing flap, another method for increasing lift is circulation control, and circulation control refers in wing
Upper to improve circular rector by the methods of air blowing, to greatly improve lift, the rear of typical circulation control wing is provided with arc
Curved surface, arc-shaped curved surface front are provided with air blowing seam, and air-flow is blown out from seam of blowing, and forms a thin layer high-speed flow, imitate in Coanda
Under the action of answering, arcuately curved surface is flowed and is attached on curved surface air-flow, is separated after flowing to certain position, the jet stream while band
Air-flow near moving deflects, and circular rector is significantly increased to the effect of washing under the air for flowing through aerofoil surface in the final wing that increases,
To increase lift, circulation control need to make in the rear setting arc-shaped curved surface of wing to generate Coanda effect its rear compared with
Thickness, when not needing high lift device during aircraft cruise, thicker rear can generate very big resistance.
The generally simple seamless wing flap of the high lift device being arranged on existing supersonic airfoil or slotted flap, when use
It deflects down, due to supersonic wing aspect ratio very little, profile thickness is very thin, even if wing flap is unfolded, what lift coefficient improved
Degree is also extremely limited, while the very thin thickness of supersonic airfoil, the slotted flap that subsonic speed passenger plane uses since structure is complicated,
It is bulky, it can not be applied on supersonic airfoil, same reason, circulation control is due to needing that arc is arranged in airfoil trailing edge
Curved surface needs thicker aerofoil profile, can not also be applied to supersonic airfoil.
Therefore problem to be solved by this invention is that supersonic wing lift under lower-speed state is smaller, while supersonic speed machine
The wing is not available the problem of means such as circulation control improve lift since thickness is too thin.
Summary of the invention
In view of the above-mentioned deficiencies, the present invention provides a kind of in such a way that wing deformation is in conjunction with circulation control technology,
Lower-speed state lower wing rear can be bent, while be equipped with seam of blowing in upper surface, blown out the jet layer of high speed, utilized Coanda
Circular rector is significantly increased in effect, so that lift coefficient is improved, while rear keeps straight under cruising condition, does not destroy wing shapes,
It not will increase additional resistance, while increasing high-lift leading-edge device, to reduce up-front air-flow separation, to improve lift system
Number.
The invention provides the following technical scheme:
A kind of circulation control deformation wing flap for supersonic wing, comprising: high-lift leading-edge device, blow seam and deformation wing flap,
It is characterized in that: the high-lift leading-edge device is placed in the front end of wing, the narrow slit that seam is strip of blowing, span-wise length with
It is close to deform wing flap, air blowing seam position is located above deformation wing flap, and is close to deform wing flap, and the deformation wing flap is equipped with
Cruising condition and two kinds of different shapes of lower-speed state.
The high-lift leading-edge device includes that droope snoot or leading edge flowing control spout, the droope snoot are located at wing
Leading edge, forward downward overturning, not only increases wing area, but also increase the camber of wing section, therefore has good lift-rising effect,
The leading edge flowing control spout is placed in the leading edge of a wing, slows down up-front air-flow separation with this.
The deformable wing flap is located at trailing edge, and is less than wing length, and the deformable wing flap is in aircraft low speed
It is flexible at crescent when state of flight, circular rector or lift are generated by the wall attachment effect for the jet stream drawn at rear；
The deformable wing flap keeps straightened condition in aircraft cruising condition, and deformable wing flap is kept horizontal under the state
State, resistance suffered by aircraft when effectively reducing cruise；
Air blowing seam position is located at deformable wing flap front end, and is close to deformable wing flap, and gas source is equipped in seam of blowing, described
Gas source can be the jet layer and wing flap for the seam blowout that makes to blow from engine bleed, air compressor or compressed air bottle etc.
Upper surface is tangent, while seam blowout high-speed jet layer of blowing, and due to the presence of Coanda effect, arcuately curved surface flows simultaneously air-flow
It is attached on curved surface, is separated after flowing to certain position, which drives neighbouring air-flow to deflect simultaneously, finally increases machine
Circular rector is significantly increased to the effect of washing under the air for flowing through aerofoil surface in the wing, to increase lift.
The deformation wing flap uses marmem, piezoelectric material, eccentric beam driving mechanism, corrugated structure etc..
The invention has effective effect that: structure is simple, does not need to increase wing thickness, is suitable for supersonic speed thin airfoil, can
To greatly improve lift coefficient of the supersonic wing under lower-speed state, the present invention is by way of deformation, under lower-speed state
Trailing edge can be bent, while be equipped with seam of blowing in upper surface, blow out the jet layer of high speed, using Coanda effect, substantially
Increase circular rector, to improve lift coefficient, while rear keeps straight under cruising condition, does not destroy wing shapes, not will increase
Additional resistance.
Figure of description
Fig. 1 is present invention form in cruising condition；
Fig. 2 is present invention form in lower-speed state；
Fig. 3 is high-lift leading-edge device detail view of the present invention；
Fig. 4 is that circulation control of the present invention deforms wing flap flow field trace distribution map；
Fig. 5 is leading edge air blowing of the present invention flow field trace distribution map；
Fig. 6 is rear air blowing of the present invention flow field trace distribution map；
Fig. 7 is plain flap flow field trace distribution map of the present invention；
Fig. 8 is different wing flap lift coefficient comparison diagrams；
In figure, 1, wing；2, gas source；3, it blows and stitches；4, Variable Geometry Wing；5, high-lift leading-edge device；6, droope snoot；7, leading edge stream
Dynamic control spout.
Specific embodiment
As depicted in figs. 1 and 2, a kind of circulation control for supersonic wing deforms wing flap, comprising: blow seam 3 and change
Shape wing flap 4, it is characterized in that: the narrow slit that seam 2 is strip of blowing, span-wise length is identical as deformation wing flap 4, the deformation
Wing flap 4 is equipped with cruising condition and two kinds of different shapes of lower-speed state；
High-lift leading-edge device 5 is set in the leading edge of supersonic wing, using the compressed air or combustion gas stream drawn from engine, is led to
The leading edge flowing for crossing 6 rear of droope snoot controls spout 7 along the entire span rearwardly and upwardly with high speed ejection, forms a piece of jet
Curtain, to play the role of the lift-rising of wing flap.
Wing flap made of one section of deformable material is set in the rear of supersonic wing, deforms to be arranged above wing flap 4 and blow
Seam 3 keeps the jet layer of 3 blowout of air blowing seam and deformation 4 upper surface of wing flap tangent.
When aircraft is in cruising condition, deformation wing flap 4 keeps straightened condition, will not bring additional resistance；
When aircraft is in lower-speed state, such as the take-off and landing stage, deformation wing flap portion 4, which divides, bends to crescent, blows at this time
Gas source 2 works in air cleft 3, and by blowing, seam 3 projects high-speed jet layer, and due to the presence of Coanda effect, air-flow is arcuately bent
Surface current is moved and is attached on curved surface, is separated after flowing to certain position, which drives neighbouring air-flow to deflect simultaneously, most
Increase wing eventually to the effect of washing under the air for flowing through aerofoil surface, the wing flap of crescent is equivalent to circulation control technology at this time
Arc-shaped rear.This process considerably increases the circular rector of wing, improves lift coefficient.
It is simulated using flow field of the Fluid Mechanics Computation method to aerofoil profile, and records the lift system under different working condition
Number, Fig. 4, Fig. 5, Fig. 6 respectively show flow field trace distribution map of the aerofoil profile used in the present invention under 0.15 Mach of speed, can
See after air-flow flows through aerofoil profile and significantly deflect down, generates compared with lift, wherein Fig. 5 and Fig. 6 illustrates leading edge and rear spray
The air-flow that mouth sprays.
Fig. 7 illustrates flow field when common dirty deflection, it is seen that the degree that aerofoil profile rear gas stream deflects down is remote
Less than Fig. 4, illustrate that the amplitude that its lift improves is less than circulation control deformation wing flap.
In order to accurately compare the lift coefficient under different conditions, calculated under each operating condition using Fluid Mechanics Computation method
Lift coefficient, such as Fig. 8, wherein the wing angle of attack is 0 degree, wind speed be 0.15 Mach, plain flap at 15 degree of deflection, improve
Lift coefficient be 0.756, and deforming wing flap under no air blowing state is 1.586, increases leading edge and when rear is blown is
2.224, it is seen then that lift coefficient can be increased considerably using method provided by the invention.
As known by the technical knowledge, the present invention can not depart from the embodiment party of its theoretical essence or essential feature by others
Case realizes that therefore, concrete scheme mentioned above is merely illustrative, and not the only, design method of the invention is suitable
The design of the trailing edge of the aircraft with supersonic flight ability for any size, it is all in the claims in the present invention
Protection scope in or the change that is equal in protection scope of the present invention be included in the invention.
Claims (7)
1. a kind of circulation control for supersonic wing deforms wing flap, comprising: high-lift leading-edge device (5), blow seam (3) and change
Shape wing flap (4), it is characterized in that: the high-lift leading-edge device (5) is placed in the front end of wing, the seam (3) of blowing is strip
Narrow slit, span-wise length is close with deformation wing flap (4), and the air blowing seam (3) position is located above deformation wing flap (4), and tight
Patch deformation wing flap (4), the deformation wing flap (4) are equipped with cruising condition and two kinds of different shapes of lower-speed state.
2. a kind of circulation control for supersonic wing according to claim 1 deforms wing flap, it is characterized in that: described blow
Gas source (2) are equipped in air cleft (3), the gas source (2) can be from engine bleed, air compressor or compressed air bottle
Deng.
3. a kind of circulation control for supersonic wing according to claim 1 deforms wing flap, it is characterized in that: the change
Shape wing flap (4) is flexible at crescent in aircraft low-speed condition.
4. a kind of circulation control for supersonic wing according to claim 1 deforms wing flap, it is characterized in that: the change
Shape wing flap (4) keeps straightened condition in aircraft cruising condition.
5. a kind of circulation control for supersonic wing according to claim 1 deforms wing flap, it is characterized in that: the change
Shape wing flap (4) is located at wing (1) rear, and is less than the spanwise length of wing (1).
6. a kind of circulation control for supersonic wing according to claim 1 deforms wing flap, it is characterized in that: before described
Edge high lift device includes that droope snoot (6) or leading edge flowing control spout (7), the droope snoot (6) are located at the leading edge of a wing,
Leading edge flowing control spout (7) is placed in the leading edge of a wing.
7. a kind of circulation control for supersonic wing according to claim 1 deforms wing flap, it is characterized in that: the change
Shape wing flap (4) uses marmem, piezoelectric material, eccentric beam driving mechanism, corrugated structure etc..
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910079375.4A CN109665090B (en) | 2019-01-28 | 2019-01-28 | Annular quantity control deformation flap for supersonic wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910079375.4A CN109665090B (en) | 2019-01-28 | 2019-01-28 | Annular quantity control deformation flap for supersonic wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109665090A true CN109665090A (en) | 2019-04-23 |
| CN109665090B CN109665090B (en) | 2023-08-15 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910079375.4A Active CN109665090B (en) | 2019-01-28 | 2019-01-28 | Annular quantity control deformation flap for supersonic wing |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113942630A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Airfoil surface for generating lift force and thrust force based on airflow ejection effect and aircraft |
| CN115180118A (en) * | 2022-08-02 | 2022-10-14 | 中国航空研究院 | High lift wing with joint jet flow control |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3525576A (en) * | 1969-03-10 | 1970-08-25 | Pierre Rene Leon Bernard Doran | Jet flap control |
| FR2572705A1 (en) * | 1984-11-08 | 1986-05-09 | Voisin Rene | Aerodynamic lift-augmenting device. |
| CN102781774A (en) * | 2009-12-23 | 2012-11-14 | 空中客车运作有限责任公司 | Aircraft with a control device |
| CN108001669A (en) * | 2017-12-05 | 2018-05-08 | 厦门大学 | A kind of leading edge slat noise suppressing method based on zero-net-mass-flux jet control |
| CN209776789U (en) * | 2019-01-28 | 2019-12-13 | 李少泽 | ring volume control deformation flap for supersonic wing |
-
2019
- 2019-01-28 CN CN201910079375.4A patent/CN109665090B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3525576A (en) * | 1969-03-10 | 1970-08-25 | Pierre Rene Leon Bernard Doran | Jet flap control |
| FR2572705A1 (en) * | 1984-11-08 | 1986-05-09 | Voisin Rene | Aerodynamic lift-augmenting device. |
| CN102781774A (en) * | 2009-12-23 | 2012-11-14 | 空中客车运作有限责任公司 | Aircraft with a control device |
| CN108001669A (en) * | 2017-12-05 | 2018-05-08 | 厦门大学 | A kind of leading edge slat noise suppressing method based on zero-net-mass-flux jet control |
| CN209776789U (en) * | 2019-01-28 | 2019-12-13 | 李少泽 | ring volume control deformation flap for supersonic wing |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113942630A (en) * | 2021-10-09 | 2022-01-18 | 中国直升机设计研究所 | Airfoil surface for generating lift force and thrust force based on airflow ejection effect and aircraft |
| CN113942630B (en) * | 2021-10-09 | 2023-04-28 | 中国直升机设计研究所 | Airfoil and aircraft capable of generating lift force and thrust force based on airflow injection effect |
| CN115180118A (en) * | 2022-08-02 | 2022-10-14 | 中国航空研究院 | High lift wing with joint jet flow control |
| CN115180118B (en) * | 2022-08-02 | 2023-05-19 | 中国航空研究院 | High-lift wing with combined jet control |
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| Publication number | Publication date |
|---|---|
| CN109665090B (en) | 2023-08-15 |
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