CN103303469A - Device for controlling flow separation caused by interference between high-Mach-number shock waves and boundary layers - Google Patents

Device for controlling flow separation caused by interference between high-Mach-number shock waves and boundary layers Download PDF

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Publication number
CN103303469A
CN103303469A CN2013102826492A CN201310282649A CN103303469A CN 103303469 A CN103303469 A CN 103303469A CN 2013102826492 A CN2013102826492 A CN 2013102826492A CN 201310282649 A CN201310282649 A CN 201310282649A CN 103303469 A CN103303469 A CN 103303469A
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trailing edge
wedge
boundary
vortex generator
shock wave
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CN103303469B (en
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李伟鹏
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Shanghai Jiaotong University
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Shanghai Jiaotong University
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    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/10Drag reduction

Abstract

The invention discloses a device for controlling flow separation caused by interference between high-Mach-number shock waves and boundary layers in the technical field of hypersonic flight vehicles. The device comprises a base flow-dividing wedge and a miniature trailing edge vortex generator, wherein the base flow-dividing wedge in a lean-back wedged structure is arranged at the front end of a shock wave and boundary layer interference region, and the distance, in particular the distance between a trailing edge and a shock wave incidence point, is smaller than or equal to the thickness of three boundary layers; the miniature trailing edge vortex generator is arranged on the upper surface of the trailing edge of the base flow-dividing wedge. According to the device, a dropping vortex structure can be generated on the side edge of the flow-dividing wedge to take away a low-energy fluid of the interference region, and a high-turbulivity shearing layer on the trailing edge serves as a buffer strip. The device can control the flow separation caused by the interference between the shock waves and the boundary layers, realizes separation flow control under the condition of Mach number of 4 to 10, and has the characteristics of simple structure, stable performance and the like.

Description

Control the device that high Mach number shock wave separates with the boundary-layer Interference Flow
Technical field
What the present invention relates to is a kind of in the hypersonic aircraft technical field, the device that separates with the boundary-layer Interference Flow of control shock wave specifically is a kind of by-pass type, have the device that the high Mach number shock wave of control of compound vortex producer separates with the boundary-layer Interference Flow.
Background technology
Hypersonic aircraft is to realize one of military strike fast, rapid-action strategy equipment, quite is subjected to domestic and international researchist's concern in recent years.Shock wave and boundary-layer disturb in the interior stream and outflow that extensively is present in high hypersonic aircraft, when aircraft during in the flight of high Mach number, intense shock wave and boundary-layer disturb the large scale flow separation that usually causes boundary-layer, supervene stronger additional resistance and pitot loss, turbulence intensity behind the shock wave and coefficient of thermal conductivity increase severely simultaneously, and having the low-frequency oscillation characteristic, the dynamic aerodynamic force/thermal load of bringing out may cause the structural failure of aircraft or the actual effect of thermal protection system.This shows, it is the potential safety hazard of hypersonic aircraft that shock wave under the high Mach number/boundary-layer disturbs the flow separation phenomenon that causes, be the key factor that influences aircraft integral body and critical component safety thereof, and bring difficulty and challenge for material selection, structure assembling and the thermal protection design of aircraft.
Vortex generator is a kind of controlled control method that delays or suppress shock wave/boundary-layer Interference Flow separation, but under high Mach number (4<M<10), because the increase of shock strength, traditional vortex generator is difficult to bring into play excellent control effect, and its major cause is that the whirlpool disturbance that traditional vortex generator produces is difficult to overcome the adverse pressure gradient that intense shock wave causes.Therefore the apparatus and method that propose the shock wave/boundary-layer Interference Flow separation under the high Mach number condition of a kind of control simple and reliable, easy realization are problem demanding prompt solutions.
Find through the retrieval to prior art, Chinese patent literature CN201210319468, open day 2013-01-09, put down in writing a kind ofly be used to making fluid flow through the vortex generator of the flow separation decay during the surface, described vortex generator is configured for neighbouring surface and produces at least two vortexs.But the defective that this technology is compared with the present invention is: be not suitable for hypersonic fluid, the structure of its vortex generator can produce stronger drag due to shock wave; The shear layer that can not strengthen the vortex generator trailing edge mixes, and is difficult to control preferably the flow analysis phenomenon of shock wave and boundary-layer interference.
Chinese patent literature CN201110322560, open day 2012-05-16, put down in writing a kind of wind turbine blade that comprises vortex generator, the structure of described vortex generator and the aerodynamic characteristics that is arranged as described blade have contribution, described vortex generator comprises platform and extension, and platform is fixed in the described depression.But under high Mach number condition, this vortex generator can not produce whirlpool disturbance preferably, can not play the effect of control shock wave flow separation.
Summary of the invention
The present invention is directed to the prior art above shortcomings, a kind of device that high Mach number shock wave separates with the boundary-layer Interference Flow of controlling is proposed, can control hypersonic speed shock wave/boundary-layer and disturb the flow separation that causes, realize the separated flow control of Mach number under 4~10 conditions, have characteristics such as simple in structure, stable performance.
The present invention is achieved by the following technical solutions, the present invention includes: base portion shunting wedge and the miniature vortex generator of trailing edge, wherein: base portion shunting wedge is the layback wedge structure, be arranged at the front end of shock wave and boundary-layer interference range, the distance of its trailing edge and shock wave point of incidence is smaller or equal to the thickness of 3 boundary-layers, and the miniature vortex generator of trailing edge is arranged at the upper surface of base portion shunting wedge trailing edge.
The front and rear edges height H of described base portion shunting wedge 2, H 1And the condition that width D and length L satisfy respectively is:
0≤H 2≤ H 1≤ δ; 2H 1≤ D≤5H 14H 1≤ L≤10H 1Wherein: δ is the thickness of incoming flow boundary-layer.
The miniature vortex generator of described trailing edge adopts an eddy current generating unit or a plurality of eddy current generating unit to arrange formation, and wherein: the horizontal maximum height h of each eddy current generating unit and axial extreme length l satisfy: 0≤h≤0.3H 10≤l≤0.5H 1And can regulate according to concrete trailing edge vortex generator different structure.
The shape of described trailing edge eddy current generating unit adopts but is not limited to cylindrical, serration, layback type wedge shape, proclined wedge structure.
The spread pattern of described trailing edge eddy current generating unit adopts the center shaft symmetrical manner, more preferably axially vertical single a plurality of modes, double alignment thereof, double arrangement mode such as staggered.
Technique effect
With respect to traditional vortex generator, the technique effect of the by-pass type that the present invention relates to, compound vortex producer comprises:
1) because shunt effect, lateral margin at base portion shunting wedge forms the unstable state turbulent structure, can periodically disturb the whirlpool of separating of causing that mutual action takes place with shock wave/boundary-layer, sweep away near the low energy fluid of interference range, increase the degeneration-resistant pressure degree of shock wave/boundary-layer interference range;
2) because the effect of trailing edge vortex generator, behind the trailing edge of incoming flow through the shunting wedge, form three-dimensional, the strong turbulent shear layer that mixes, the turbulent shear layer plays well " alleviating band " effect, be used for weakening shock wave and be directly incident on strong adverse pressure gradient on the wall, shunt the expansion wave system that the wedge trailing edge forms simultaneously, be conducive to accelerate the turbulent shear layer, the momentum that overcomes behind the shock wave front is poor.
With respect to traditional vortex generator, the present invention has three kinds of advantages:
1) by-pass type, compound vortex producer have strong shunt effect, have strengthened degree of irregularity and the degeneration-resistant pressure degree of turbulent boundary layer, and the intensity of shunting action can be regulated by the leading edge height that base portion is shunted wedge;
2) base portion is shunted the large scale of the lateral margin formation of wedge, the whirlpool structure of periodic swinging, is conducive to take away the low energy fluid of interference range;
3) by the combination of shunting wedge and miniature vortex generator, significantly strengthened the turbulence intensity of trailing edge shear layer, make the disturbance rejection intensity enhancing.
Description of drawings
Fig. 1 is vortex generator structural representation among the embodiment 1.
Fig. 2 is vortex generator structural representation among the embodiment 2.
Fig. 3 is vortex generator structural representation among the embodiment 3.
Fig. 4 is vortex generator structural representation among the embodiment 4.
Fig. 5 is vortex generator structural representation among the embodiment 5.
Fig. 6 is vortex generator structural representation among the embodiment 6.
The specific embodiment
Below embodiments of the invention are elaborated, present embodiment is being to implement under the prerequisite with the technical solution of the present invention, provided detailed embodiment and concrete operating process, but protection scope of the present invention is not limited to following embodiment.
Embodiment 1
As shown in Figure 1, the present embodiment device comprises: base portion shunting wedge 1 and the miniature vortex generator 2 of trailing edge, wherein: the base portion shunting wedge 1 of layback wedge structure is arranged at the front end of shock wave and boundary-layer interference range and smaller or equal to the thickness of 3 boundary-layers, the miniature vortex generator 2 of trailing edge is arranged at the trailing edge of base portion shunting wedge 1 apart from (specifically shunting the wedge trailing edge to shock wave point of incidence distance).
The front and rear edges height H of described base portion shunting wedge 1 2, H 1And width D and length L satisfy respectively: 0≤H 2≤ H 1≤ δ; 2H 1≤ D≤5H 14H 1≤ L≤10H 1Wherein: δ is the thickness of incoming flow boundary-layer.
As shown in Figure 1, the miniature vortex generator 2 of the trailing edge in the present embodiment adopts three eddy current generating units 2 axially vertical, namely along the single arrangement of Z-direction.
Described eddy current generating unit 3 adopts cylindrical structural, and the horizontal maximum height h of each eddy current generating unit 2 and axial extreme length l satisfy: 0≤h≤0.3H 10≤l≤0.5H 1And can regulate according to concrete trailing edge vortex generator different structure.
Under high Mach number condition because the enhancing of shock strength, cause producing at shock wave point of incidence annex the large scale flow separation of boundary-layer, utilize the mobile control action of device shown in Figure 1, can eliminate the flow separation phenomenon at the lateral margin of shunting wedge and the vortex structure of trailing edge generation, avoid because many counter productives that flow separation causes.
Embodiment 2
As shown in Figure 2, present embodiment is with the difference of embodiment 1: the miniature vortex generator 2 of described trailing edge adopts two eddy current generating units 2 axially vertical, namely along the single arrangement of Z-direction; And described eddy current generating unit 2 adopts the shape wedge structure that leans forward.
The shape and structure technical requirements details of this eddy current generating unit 2 is: trailing edge height h, the width d of described eddy current generating unit 2 and length l satisfy respectively: 0≤h≤0.3H 1H≤d≤2h; H≤l≤3h.
The control effect of present embodiment under high Mach number condition is similar to embodiment 1.
Embodiment 3
As shown in Figure 3, present embodiment is with the difference of embodiment 1: the miniature vortex generator 2 of described trailing edge adopts two eddy current generating units 2 axially vertical, namely along the single arrangement of Z-direction; And described eddy current generating unit 2 adopts layback shape wedge structure.
The shape and structure technical requirements details of this eddy current generating unit 2 is: leading edge height h, the width d of described eddy current generating unit 2 and length l satisfy respectively: 0≤h≤0.3H 1H≤d≤2h; H≤l≤3h.
The control effect of present embodiment under high Mach number condition is similar to embodiment 1.
Embodiment 4
As shown in Figure 4, present embodiment is with the difference of embodiment 1: the miniature vortex generator 2 of described trailing edge adopts two eddy current generating units 2 axially vertical, namely along the single arrangement of Z-direction; And described eddy current generating unit 2 adopts the depression broached-tooth design.
The shape and structure technical requirements details of this eddy current generating unit 2 is: trailing edge height h, the width d of described eddy current generating unit 2 and length l satisfy respectively: 0≤h≤0.3H 1H≤d≤2h; H≤l≤3h.
The control effect of present embodiment under high Mach number condition is similar to embodiment 1.
Embodiment 5
As shown in Figure 5, present embodiment is with the difference of embodiment 1: the miniature vortex generator 2 of described trailing edge adopts 6 eddy current generating units 2 axially vertical, and namely double alignment is arranged along Z axle side;
Distance of shaft centers between the double eddy current generating unit 2 from the parameter request of DX is: l≤DX≤2l.
Present embodiment is than embodiment 1, can strengthen the shear layer mixed effect to shunting wedge trailing edge, better suppresses the flow analysis phenomenon that shock wave causes, but may cause the bigger resistance than embodiment 1.
Embodiment 6
As shown in Figure 6, present embodiment is with the difference of embodiment 1: the miniature vortex generator 2 of described trailing edge adopts 5 eddy current generating units 2 axially vertical, namely is staggered along Z axle side is double;
Distance of shaft centers between the double eddy current generating unit 2 from the parameter request of DX is: l≤DX≤3l.
Present embodiment is than embodiment 1, can strengthen the shear layer mixed effect to shunting wedge trailing edge, better suppresses the flow analysis phenomenon that shock wave causes, but may cause the bigger resistance than embodiment 1.

Claims (6)

1. one kind is used for the device that the high Mach number shock wave of control separates with the boundary-layer Interference Flow, it is characterized in that, comprise: base portion shunting wedge and the miniature vortex generator of trailing edge, wherein: the base portion shunting of layback wedge structure wedges front end and the distance that places shock wave and boundary-layer interference range, be that trailing edge is to the distance of shock wave point of incidence, smaller or equal to the thickness of 3 boundary-layers, the miniature vortex generator of trailing edge is arranged at the trailing edge of base portion shunting wedge.
2. device according to claim 1 is characterized in that, the front and rear edges height H of described base portion shunting wedge 2, H 1And the condition that width D and length L satisfy respectively is: 0≤H 2≤ H 1≤ δ; 2H 1≤ D≤5H 14H 1≤ L≤10H 1Wherein: δ is the thickness of incoming flow boundary-layer.
3. device according to claim 1, it is characterized in that, the miniature vortex generator of described trailing edge adopts an eddy current generating unit or a plurality of eddy current generating unit to arrange formation, and wherein: the horizontal maximum height h of each eddy current generating unit and axial extreme length l satisfy: 0≤h≤0.3H 10≤l≤0.5H 1, wherein: H 1Trailing edge height for base portion shunting wedge.
4. device according to claim 3 is characterized in that, that the shape of described eddy current generating unit adopts is cylindrical, serration, layback type wedge shape or proclined wedge structure.
5. device according to claim 3 is characterized in that, the center shaft symmetrical manner is adopted in described arrangement.
6. device according to claim 3 is characterized in that, axially vertical single a plurality of modes, axially vertical double alignment thereof or double arrangement mode such as staggered are adopted in described arrangement.
CN201310282649.2A 2013-07-05 2013-07-05 Device for controlling flow separation caused by interference between high-Mach-number shock waves and boundary layers Expired - Fee Related CN103303469B (en)

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106323588A (en) * 2016-10-12 2017-01-11 南京航空航天大学 Device and method for rapid development of boundary layer in supersonic flow field
CN107074344A (en) * 2017-01-13 2017-08-18 深圳市大疆创新科技有限公司 Propeller, power suit and the unmanned plane of aircraft
CN109436421A (en) * 2018-11-06 2019-03-08 方祥杰 A kind of preparation method of the excessively high part flow arrangement of redried leaf tobacco
CN111120461A (en) * 2020-01-19 2020-05-08 中国人民解放军海军工程大学 Underwater flow excitation cavity noise control device
CN112173082A (en) * 2020-08-25 2021-01-05 中国航天空气动力技术研究院 Micro-vortex generating device with auxiliary control of airflow
CN114148508A (en) * 2021-12-28 2022-03-08 中国航天空气动力技术研究院 Control device for inhibiting boundary layer interference flow separation
CN114590418A (en) * 2022-03-09 2022-06-07 厦门大学 Method and device for inhibiting surface pulsating pressure of high-speed aircraft
CN114735203A (en) * 2022-06-13 2022-07-12 中国空气动力研究与发展中心高速空气动力研究所 Noise suppression device for triangular prism-shaped aircraft weapons cabin

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0845580A2 (en) * 1993-12-28 1998-06-03 Kabushiki Kaisha Toshiba A heat transfer promoting structure
WO2000015961A1 (en) * 1998-09-16 2000-03-23 Lm Glasfiber A/S Wind turbine blade with vortex generator
WO2011004262A1 (en) * 2009-07-10 2011-01-13 Ireland Peter S Elastomeric vortex generators
US20110315248A1 (en) * 2010-06-01 2011-12-29 Simpson Roger L Low drag asymmetric tetrahedral vortex generators
CN102865274A (en) * 2011-07-09 2013-01-09 拉姆金动力系统有限责任公司 Vortex generators

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0845580A2 (en) * 1993-12-28 1998-06-03 Kabushiki Kaisha Toshiba A heat transfer promoting structure
WO2000015961A1 (en) * 1998-09-16 2000-03-23 Lm Glasfiber A/S Wind turbine blade with vortex generator
WO2011004262A1 (en) * 2009-07-10 2011-01-13 Ireland Peter S Elastomeric vortex generators
US20110315248A1 (en) * 2010-06-01 2011-12-29 Simpson Roger L Low drag asymmetric tetrahedral vortex generators
CN102865274A (en) * 2011-07-09 2013-01-09 拉姆金动力系统有限责任公司 Vortex generators

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106323588A (en) * 2016-10-12 2017-01-11 南京航空航天大学 Device and method for rapid development of boundary layer in supersonic flow field
CN107074344A (en) * 2017-01-13 2017-08-18 深圳市大疆创新科技有限公司 Propeller, power suit and the unmanned plane of aircraft
CN107074344B (en) * 2017-01-13 2018-09-25 深圳市大疆创新科技有限公司 Propeller, power suit and the unmanned plane of aircraft
CN109436421A (en) * 2018-11-06 2019-03-08 方祥杰 A kind of preparation method of the excessively high part flow arrangement of redried leaf tobacco
CN111120461A (en) * 2020-01-19 2020-05-08 中国人民解放军海军工程大学 Underwater flow excitation cavity noise control device
CN111120461B (en) * 2020-01-19 2021-09-28 中国人民解放军海军工程大学 Underwater flow excitation cavity noise control device
CN112173082A (en) * 2020-08-25 2021-01-05 中国航天空气动力技术研究院 Micro-vortex generating device with auxiliary control of airflow
CN112173082B (en) * 2020-08-25 2021-11-16 中国航天空气动力技术研究院 Micro-vortex generating device with auxiliary control of airflow
CN114148508A (en) * 2021-12-28 2022-03-08 中国航天空气动力技术研究院 Control device for inhibiting boundary layer interference flow separation
CN114590418A (en) * 2022-03-09 2022-06-07 厦门大学 Method and device for inhibiting surface pulsating pressure of high-speed aircraft
CN114590418B (en) * 2022-03-09 2023-10-24 厦门大学 Method and device for suppressing surface pulsation pressure of high-speed aircraft
CN114735203A (en) * 2022-06-13 2022-07-12 中国空气动力研究与发展中心高速空气动力研究所 Noise suppression device for triangular prism-shaped aircraft weapons cabin

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