CN115123517A - Controllable big stall angle of attack wing structure based on ground floor - Google Patents
Controllable big stall angle of attack wing structure based on ground floor Download PDFInfo
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- CN115123517A CN115123517A CN202210617782.8A CN202210617782A CN115123517A CN 115123517 A CN115123517 A CN 115123517A CN 202210617782 A CN202210617782 A CN 202210617782A CN 115123517 A CN115123517 A CN 115123517A
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- 238000000926 separation method Methods 0.000 description 4
- 230000001276 controlling effect Effects 0.000 description 3
- 230000003111 delayed effect Effects 0.000 description 2
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- 238000002347 injection Methods 0.000 description 2
- 239000007924 injection Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002596 correlated effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
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- 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
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Abstract
The invention discloses a controllable large stall attack angle wing structure based on a ground floor, which comprises: the device comprises a controller, a driving motor and a wing; the upper part of the front end of the wing is provided with a mounting groove; the controller and the driving motor are both arranged in the mounting groove; the controller is connected with the driving motor. The invention greatly increases the stall attack angle.
Description
Technical Field
The invention belongs to the technical field of wings, and particularly relates to a controllable large-stall attack angle wing structure based on a ground layer.
Background
In the wing surface flow-around, the lift force and the resistance of the wing increase along with the increase of the attack angle, when a critical attack angle value is reached, the stall phenomenon occurs, the lift force suddenly drops, the resistance greatly rises, and the serious flow separation phenomenon is accompanied. The phenomenon is widely existed in parts such as wings, vane type hydraulic machinery, wind turbines, centrifugal compressors and the like, and the performance and the efficiency of the wings are reduced due to the generation of stall, so that the safe and stable operation of related parts is influenced. In recent years, the problem of stalling has become a hot problem, and has attracted extensive attention from scholars and engineers. How to effectively suppress the loss of speed is the current direction of intensive research.
The traditional method for improving the stall critical attack angle is to add passive devices (vortex generators, Gurney flaps and the like) on the outer surface of the wing body, but the devices bring extra resistance under the condition of small attack angle, so that the extra resistance is not paid. In addition, the active flow control methods such as synthetic jet, plasma excitation, suction control and the like mainly control the local flow of a flow field near the wing to delay flow separation and improve aerodynamic performance. However, the method does not need to add additional equipment such as air channels, controllers, actuators and power supplies, and simultaneously needs external energy input, thereby increasing the weight and energy loss of the aircraft.
Disclosure of Invention
The invention solves the technical problems that: the defects of the prior art are overcome, the controllable large-stall-angle-of-attack wing structure based on the ground layer is provided, and the stall angle-of-attack is increased to the greatest extent by controlling the boundary layer.
The purpose of the invention is realized by the following technical scheme: a ground-based controllable large stall angle of attack wing structure, comprising: the device comprises a controller, a driving motor and a wing; wherein, the upper part of the front end of the wing is provided with a mounting groove; the controller and the driving motor are both arranged in the mounting groove; the controller is connected with the driving motor.
In the ground-based controllable wing structure with the large stall attack angle, the controller comprises a rotating shaft and a plurality of blades; wherein, a plurality of blades are connected with the circumferential end of the rotating shaft; the blades are uniformly distributed along the circumferential direction of the rotating shaft.
In the above ground-based controllable large stall angle of attack wing structure, the controller further comprises a drive shaft; one end of the driving shaft is connected with the rotating shaft, and the other end of the driving shaft is connected with the driving motor.
Among the above-mentioned controllable big stall angle of attack wing structure based on ground floor, still include: a drive motor mounting base; the driving motor is arranged in the mounting groove through the driving motor mounting seat.
In the ground-floor-based controllable large-stall attack-angle wing structure, the ratio of the span length L2 of the wing to the width L7 of the controller is 3-5.
In the ground-based controllable large-stall attack-angle wing structure, the ratio of the distance L4 between the center of the controller and the leading edge to the chord length L5 of the wing is 0.15-0.32.
In the ground-floor-based controllable large-stall attack-angle wing structure, the ratio of the radius L3 of the controller to the distance L6 from the center of the rotating shaft to the surface of the wing is 1.05-1.10.
In the ground-floor-based controllable large-stall angle-of-attack wing structure, the ratio of the width L7 of the controller to the width L1 of the mounting groove is 0.98-0.99.
In the controllable large stall attack angle wing structure based on the ground floor, the height delta of the upper wall surface of the controller protruding out of the wing is 0.5-0.7 times of the thickness of the local boundary layer; wherein,
the local boundary layer thickness is obtained by the following formula:
wherein δ is the local boundary layer thickness, Re is the local reynolds number, ρ is the air density, U is the air velocity, Δ is the height of the controller from the wall surface, L4 is the distance from the center of the controller to the leading edge, and μ is the sticking coefficient.
In the above-mentioned wing structure based on ground layer controllable large stall angle of attack, the relation formula between the rotating speed of the controller and the energy injected into the local boundary layer is as follows:
E＝ρ·V 2 ；
V＝2π·r·n；
where E is the energy injected into the local boundary layer, V is the gas velocity, r is the radius of the controller, and n is the rotational speed of the controller.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention greatly increases the stalling attack angle by controlling the boundary layer.
(2) The invention can change the mode of injecting boundary layer energy to adapt to the requirements of different working conditions on the wing performance.
(3) The invention has simple control mode and small additional resistance.
Drawings
Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a top view of a controllable large stall angle of attack wing structure based on a ground floor according to an embodiment of the present invention;
FIG. 2 is a cross-sectional view of a controllable large stall angle of attack wing structure based on a ground floor according to an embodiment of the present invention;
fig. 3 is a cross-sectional view of a ground-based layer controllable large-stall angle-of-attack wing structure according to an embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the accompanying drawings in conjunction with embodiments.
FIG. 1 is a top view of a controllable large stall angle of attack wing structure based on a ground floor according to an embodiment of the present invention; FIG. 2 is a cross-sectional view of a ground-based, controllable high-stall angle-of-attack wing structure according to an embodiment of the present invention; fig. 3 is a cross-sectional view of a ground-based layer controllable large-stall angle-of-attack wing structure according to an embodiment of the present invention. As shown in fig. 1 to 3, the wing structure with large stall angle of attack controllable based on ground floor comprises: the controller 1, the driving motor 7 and the wing 2; wherein, the upper part of the front end of the wing 2 is provided with a mounting groove 5; the controller 1 and the driving motor 7 are both arranged in the mounting groove 5; the controller 1 is connected with a drive motor 7.
The rotating speed of the driving motor is controlled, so that the controller injects energy into the boundary layer of the wing at different frequencies, the anti-back pressure capability of the boundary layer is improved, the occurrence of separation is delayed, and the stall attack angle of the wing is improved.
The relationship between the rotational speed of the controller 1 and the energy injected into the local boundary layer is as follows:
E＝ρ·V 2 ；
V＝2π·r·n；
wherein E is the injection energy, V is the gas velocity, r is the radius, n is the rotation speed, and the magnitude of the injection energy in the boundary layer is positively correlated with the rotation speed.
As shown in fig. 2, the controller 1 includes a rotating shaft 4 and a plurality of blades 3; wherein, a plurality of blades 3 are connected with the circumferential end of the rotating shaft 4; the plurality of blades 3 are uniformly distributed along the circumferential direction of the rotating shaft 4. Specifically, the number of the blades 3 is 4. The boundary layer of the wing is controlled through the rotation of the controller 1, so that the separation is delayed, and the stall attack angle of the wing is improved.
As shown in fig. 2, the controller 1 further includes a drive shaft 8; wherein, one end of the driving shaft 8 is connected with the rotating shaft 4, and the other end of the driving shaft 8 is connected with the driving motor 7.
As shown in fig. 3, the ground-based layer controllable large-stall angle-of-attack wing structure further includes: a driving motor mounting base 6; wherein, the driving motor 7 is arranged in the mounting groove 5 through the driving motor mounting seat 6.
The controller 1 is mounted at the leading edge of the wing 2. The incoming flow Mach number range is 0.1-2.0, and the controller 1 can effectively control the boundary layer in the range.
The ratio of the distance L4 between the center of the controller 1 and the leading edge to the chord length L5 of the wing 2 is 0.15-0.32, and the installation position can enable the controller 1 to have the optimal control effect.
The ratio of the radius L3 of the controller 1 to the distance L6 from the center of the rotating shaft 4 to the surface of the wing is 1.05-1.10, and the distance of the blade 3 protruding out of the surface of the wing 2 is appropriate in the range, so that the controller 1 is ensured to have a good control effect, and the additional resistance is reduced as much as possible.
The ratio of the span length L2 of the wing 2 to the width L7 of the controller 1 is 3-5, and the range ensures the uniformity of the flow field in the direction of the wing 2.
The ratio of the width L7 of the controller 1 to the width L1 of the mounting groove 5 is 0.98-0.99, and the air flow entering the mounting groove 5 is reduced as much as possible.
In order to ensure small resistance introduction, the height delta of the controller protruding wall surface is 0.5-0.7 times of the thickness of the local boundary layer.
The local boundary layer thickness is obtained by the following formula:
Δ＝L3-L6；
wherein δ is the local boundary layer thickness, Re is the local reynolds number, ρ is the air density, U is the air velocity, Δ is the height of the controller's convex wall, L4 is the distance between the center of the controller and the leading edge, and μ is the sticking coefficient.
By controlling the boundary layer, the stall attack angle is increased to the maximum extent; the invention can change the mode of injecting boundary layer energy to meet the requirements of different working conditions on the performance of the wing; the invention has simple control mode and small additional resistance.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (10)
1. A controllable big stall angle of attack wing structure based on ground floor, its characterized in that includes: the device comprises a controller (1), a driving motor (7) and a wing (2); wherein,
the upper part of the front end of the wing (2) is provided with a mounting groove (5);
the controller (1) and the driving motor (7) are arranged in the mounting groove (5);
the controller (1) is connected with the driving motor (7).
2. The ground-based layer controllable large stall angle of attack wing structure of claim 1, wherein: the controller (1) comprises a rotating shaft (4) and a plurality of blades (3); wherein,
the blades (3) are connected with the circumferential end of the rotating shaft (4);
the blades (3) are uniformly distributed along the circumferential direction of the rotating shaft (4).
3. The ground floor based controllable large stall angle of attack wing structure of claim 2, wherein: the controller (1) further comprises a drive shaft (8); one end of the driving shaft (8) is connected with the rotating shaft (4), and the other end of the driving shaft (8) is connected with the driving motor (7).
4. The ground-based layer controllable large stall angle of attack wing structure of claim 1, further comprising: a driving motor mounting base (6); the driving motor (7) is arranged in the mounting groove (5) through the driving motor mounting seat (6).
5. The ground floor based controllable large stall angle of attack wing structure of claim 1, wherein: the ratio of the span length L2 of the wing (2) to the width L7 of the controller (1) is 3-5.
6. The ground-based layer controllable large stall angle of attack wing structure of claim 1, wherein: the ratio of the distance L4 between the center of the controller (1) and the leading edge to the chord length L5 of the wing (2) is 0.15-0.32.
7. The ground-based layer controllable large stall angle of attack wing structure of claim 1, wherein: the ratio of the radius L3 of the controller (1) to the distance L6 from the center of the rotating shaft (4) to the surface of the wing is 1.05-1.10.
8. The ground-based layer controllable large stall angle of attack wing structure of claim 1, wherein: the ratio of the width L7 of the controller (1) to the width L1 of the mounting groove (5) is 0.98-0.99.
9. The ground-based layer controllable large stall angle of attack wing structure of claim 1, wherein: the height delta of the controller (1) protruding out of the upper wall surface of the wing (2) is 0.5-0.7 times the thickness of the local boundary layer; wherein,
the local boundary layer thickness is obtained by the following formula:
wherein δ is the local boundary layer thickness, Re is the local reynolds number, ρ is the air density, U is the air velocity, Δ is the height of the controller's convex wall, L4 is the distance between the center of the controller and the leading edge, and μ is the sticking coefficient.
10. The ground floor based controllable large stall angle of attack wing structure of claim 1, wherein: the relation formula of the rotating speed of the controller (1) and the energy injected to the local boundary layer is as follows:
E＝ρ·V 2 ；
V＝2π·r·n；
wherein E is the energy injected into the local boundary layer, V is the gas velocity, r is the radius of the controller, and n is the rotating speed of the controller (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210617782.8A CN115123517B (en) | 2022-06-01 | 2022-06-01 | Large stall attack angle wing structure based on ground layer control |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202210617782.8A CN115123517B (en) | 2022-06-01 | 2022-06-01 | Large stall attack angle wing structure based on ground layer control |
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| CN115123517A true CN115123517A (en) | 2022-09-30 |
| CN115123517B CN115123517B (en) | 2024-08-30 |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110272529A1 (en) * | 2010-04-22 | 2011-11-10 | Terry Wayne Hamilton | Hamilton H.N2 laminar flow diskette wing |
| US20200001982A1 (en) * | 2018-07-02 | 2020-01-02 | Larry Utt | Short take off and landing aircraft with adjustable vortices device |
| CN112849389A (en) * | 2021-01-27 | 2021-05-28 | 北京理工大学 | Dynamic stall control method based on dynamic droop of wing leading edge |
| CN113120218A (en) * | 2021-05-25 | 2021-07-16 | 中国人民解放军空军工程大学 | Composite plasma excitation method for flow separation control of high-subsonic wing |
| CN114476048A (en) * | 2022-01-12 | 2022-05-13 | 南京航空航天大学 | Flange fusion propulsion structure based on rim driving technology |
-
2022
- 2022-06-01 CN CN202210617782.8A patent/CN115123517B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110272529A1 (en) * | 2010-04-22 | 2011-11-10 | Terry Wayne Hamilton | Hamilton H.N2 laminar flow diskette wing |
| US20200001982A1 (en) * | 2018-07-02 | 2020-01-02 | Larry Utt | Short take off and landing aircraft with adjustable vortices device |
| CN112849389A (en) * | 2021-01-27 | 2021-05-28 | 北京理工大学 | Dynamic stall control method based on dynamic droop of wing leading edge |
| CN113120218A (en) * | 2021-05-25 | 2021-07-16 | 中国人民解放军空军工程大学 | Composite plasma excitation method for flow separation control of high-subsonic wing |
| CN114476048A (en) * | 2022-01-12 | 2022-05-13 | 南京航空航天大学 | Flange fusion propulsion structure based on rim driving technology |
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| CN115123517B (en) | 2024-08-30 |
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