Effect on near-wall region flow by an array of dielectric barrierdischarge plasma actuators

QIN Litao; ZHANG Haideng; WANG Yizhou

doi:10.7638/kqdlxxb-2021.0068

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

Effect on near-wall region flow by an array of dielectric barrierdischarge plasma actuators

更新时间：2026-05-28

- Effect on near-wall region flow by an array of dielectric barrierdischarge plasma actuators
- Vol. 40, Issue 2, Pages: 50-58(2022)
- 作者机构：
  
  空军工程大学等离子体动力学重点实验室,西安,710038
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0068
  CLC： O539
- Published：2022
- 稿件说明：
移动端阅览
秦立涛, 张海灯, 汪一舟. 阵列式介质阻挡放电等离子体激励对近壁区流动影响[J]. 空气动力学学报, 2022, 40(2): 50−58.

QIN Litao, ZHANG Haideng, WANG Yizhou. Effect on near-wall region flow by an array of dielectric barrierdischarge plasma actuators[J]. 2022, 40(2): 50-58.
秦立涛, 张海灯, 汪一舟. 阵列式介质阻挡放电等离子体激励对近壁区流动影响[J]. 空气动力学学报, 2022, 40(2): 50−58. DOI： 10.7638/kqdlxxb-2021.0068

QIN Litao, ZHANG Haideng, WANG Yizhou. Effect on near-wall region flow by an array of dielectric barrierdischarge plasma actuators[J]. 2022, 40(2): 50-58. DOI： 10.7638/kqdlxxb-2021.0068.

摘要

为了揭示介质阻挡放电等离子体激励流场作用效果对流动状态的依赖性，设计了由八组表面介质阻挡放电等离子体激励器（AC-SDBD）组成的阵列式激励器，在来流风速20～80 m/s工况下，研究了其对近壁区流动的影响。实验结果表明：施加激励的瞬间，阵列式AC-SDBD使得近壁区速度明显增大，随着时间的推移，近壁区速度有所下降，最后趋于稳定；当流动状态稳定后，激励沿流向和法向的影响范围分别达到了激励器下游170 mm和距离壁面10 mm位置，且激励后近壁区速度分布规律与流向距离和距壁面高度均有关；来流速度较低时，激励使得稳定后的近壁区速度增大，但当来流速度增大到一定数值时，施加激励后近壁区速度有所减小。

Abstract

In order to reveal the flow state dependence of the control effect by alternating current surface dielectric barrier discharge (AC-SDBD) plasma actuation

an array of eight AC-SDBD plasma actuators was designed

and the influence on the flow in the near-wall region was investigated for the mainstream velocity ranging from 20 m/s to 80 m/s. The experimental results show that the array of AC-SDBD plasma actuators can significantly increase the velocity in the near-wall region initially

which eventually drops a bit before finally stabilizes. After the flow reaches a new stable state

the influence range of the plasma actuation can extent as far as 170 mm downstream of the actuators and 10 mm in the wall-normal direction

respectively. Moreover

the velocity distribution near the wall under the plasma actuation depends on the streamwise and wall-normal locations. When the mainstream velocity is small

the plasma actuation increases the near-wall velocity after stabilization

but when the mainstream velocity is above a certain value

the near-wall velocity after the plasma actuation is lower than the corresponding no actuated case.

关键词

Keywords

references

WU Y, LI Y H. Progress and outlook of plasma flow control[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(2): 381-405. (in Chinese).

CORKE T C, ENLOE C L, WILKINSON S P. Dielectric barrier discharge plasma actuators for flow control[J]. Annual Review of Fluid Mechanics, 2010, 42(1): 505-529.DOI: 10.1146/annurev-fluid-121108-145550.

WANG J J, CHOI K S, FENG L H, et al. Recent developments in DBD plasma flow control[J]. Progress in Aerospace Sciences, 2013, 62: 52-78. doi: 10.1016/j.paerosci.2013.05.003.

JIA Y H, LIANG H, HE Q K, et al. Flow separation control of nacelle in crosswind by microsecond pulsed surface dielectric barrier discharge plasma actuator[J]. Flow, Turbulence and Combustion, 2021: 1-21.DOI: 10.1007/s10494-021-00247-0.

KADIVAR A, AMANIFARD N, DEYLAMI H M, et al. Flow separation control in an axial compressor cascade using various arrangement of plasma actuator[J]. Journal of Electrostatics, 2021, 112: 103580. doi: 10.1016/j.elstat.2021.103580.

YATES H B, MATLIS E H, JULIANO T J, et al. Plasma-actuated flow control of hypersonic crossflow-induced boundary-layer transition[J]. AIAA Journal, 2020, 58(5): 2093-2108.DOI: 10.2514/1.J058981.

KIM D, DO H, CHOI H. Drag reduction on a three-dimensional model vehicle using a wire-to-plate DBD plasma actuator[J]. Experiments in Fluids, 2020, 61(6): 1-14.DOI: 10.1007/s00348-020-02961-3.

PEREIRA GOUVEIA DA SILVA G, EGUEA J P, GARCIA CROCE J A, et al. Slat aerodynamic noise reduction using dielectric barrier discharge plasma actuators[J]. Aerospace Science and Technology, 2020, 97: 105642.DOI: 10.1016/j.ast.2019.105642.

THOMAS F O, KOZLOV A, CORKE T C. Plasma actuators for cylinder flow control and noise reduction[J]. AIAA Journal, 2008, 46(8): 1921-1931.DOI: 10.2514/1.27821.

REECE ROTH J, DAI X. Optimization of the aerodynamic plasma actuator as an electrohydrodynamic (EHD) electrical device[C ] // 44th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virginia: AIAA, 2006. doi: 10.2514/6.2006-1203

YANG L L, LI J, CAI J S, et al. Lift augmentation based on flap deflection with dielectric barrier discharge plasma flow control over multi-element airfoils[J]. Journal of Fluids Engineering, 2016, 138(3): 031401.DOI: 10.1115/1.4031613.

ZHANG H D, WU Y, LI Y H, et al. Control of compressor tip leakage flow using plasma actuation[J]. Aerospace Science and Technology, 2019, 86: 244-255. doi: 10.1016/j.ast.2019.01.009.

WU Y, ZHANG H D, YU X J, et al. Plasma flow control of axial compressor[J]. Journal of Engineering Thermophysics, 2017, 38(7): 1396-1414. (in Chinese).

SADDOUGHI S, BENNETT G, BOESPFLUG M, et al. Experimental investigation of tip clearance flow in a transonic compressor with and without plasma actuators[C ] //Proceedings of ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, Düsseldorf, Germany. 2014. doi: 10.1115/GT2014-25294

ZHAO X H, LI Y H, WU Y, et al. Investigation on the acceleration characteristic by plasma aerodynamic actuation[J]. Acta Aerodynamica Sinica, 2010, 28(2): 168-173, 196. (in Chinese).

CHERNYSHEV S L, GAMIRULLIN M D, KURYACHII A P, et al. Simple design of multiple aerodynamic plasma actuator[C ] // Progress in Flight Physics, Krakow, Poland. Les Ulis, France: EDP Sciences, 2017. doi: 10.1051/eucass/2016090253

GAMIRULLIN M D, KURYACHII A P, LITVINOV V M, et al. Investigation of a simplified scheme of multiple plasma actuator for boundary layer control[J]. TsAGI Science Journal, 2014, 45(8): 889-901.DOI: 10.1615/tsagiscij.2015013547.

SATO S, OZAWA Y, KOMURO A, et al. Experimental demonstration of low-voltage operated dielectric barrier discharge plasma actuators using SiC MOSFETs[J]. Journal of Physics D: Applied Physics, 2020, 53(43): 43LT01.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Progress and outlook of plasma-based turbulent skin-friction drag reduction

Numerical simulation of hypersonic magnetofluid control based on non-linear coupling constitutive relation

Influence of slotted track on aerodynamic characteristics of high-speed maglev train

Research status of aerodynamic design for integrated propulsion and airframe in near-space high-altitude long-endurance (HALE) UAVs

Preface to the special column on “UAV Aero-Propulsive Integration Design”

Related Author

SU Zhi

ZONG Haohua

LIANG Hua

WU Yun

FANG Ziqi

Shi Hao

Xiao Hong

Zhou Li

Related Institution

National Key Lab of Aerospace Power System and Plasma Technology, Aviation Engineering school, Airforce Engineering University, Xi’an

School of Mechanical Engineering, Xi’an Jiaotong University, Xi’an

School of Aerospace Engineering, Xi’an Jiaotong University, Xi’an

Collaborative Innovation Center for Advanced Aero-Engine, Beijing

School of Power and Energy, Northwestern Polytechnical University, Xi'an

AI问答

⁰