基于新型丝状电极等离子体激励器的前体涡控制

高超; 倪章松; 薛明; 郑博睿

doi:10.7638/kqdlxxb-2020.0116

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基于新型丝状电极等离子体激励器的前体涡控制

研究论文 | 更新时间：2026-05-28

- 基于新型丝状电极等离子体激励器的前体涡控制
- Forebody vortex control with a wire-based DBD plasma actuator
- 空气动力学学报 2021年39卷第2期页码：39-52
- 作者机构：
  
  1. 西北工业大学航空学院,西安,710071
  2. 西安理工大学自动化与信息工程学院,西安,710048
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2020.0116
  中图分类号： O539
- 纸质出版：2021
- 稿件说明：
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高超, 倪章松, 薛明, 郑博睿. 基于新型丝状电极等离子体激励器的前体涡控制[J]. 空气动力学学报, 2021, 39(2): 39-52.

GAO Chao, NI Zhangsong, XUE Ming, et al. Forebody vortex control with a wire-based DBD plasma actuator[J]. 2021, 39(2): 39-52.
高超, 倪章松, 薛明, 郑博睿. 基于新型丝状电极等离子体激励器的前体涡控制[J]. 空气动力学学报, 2021, 39(2): 39-52. DOI： 10.7638/kqdlxxb-2020.0116.

GAO Chao, NI Zhangsong, XUE Ming, et al. Forebody vortex control with a wire-based DBD plasma actuator[J]. 2021, 39(2): 39-52. DOI： 10.7638/kqdlxxb-2020.0116.

摘要

本文首次将新型丝状暴露电极DBD等离子激励器应用于大迎角下细长体非对称涡控制。丝状暴露电极的材料的选择对DBD推力以及推力效率至关重要，通过地面精细推力测量对丝状暴露电极等离子体激励器进行了优化，结果表明，本文研究材料中采用钨丝作为暴露电极，其推力效率最优；且随着电极直径从

= 0.3 mm 减小到

= 0.08 mm，DBD推力效率显著提升。基于优化后的DBD激励器，将其应用于前体非对称涡控制：未施加等离子体控制时，压力测量以及PIV结果均表明细长体背风区流场为明显的非对称涡结构；在等离子体激励下，该非对称涡结构可变为对称甚至反向非对称，且非稳态激励控制能力明显优于稳态激励。研究发现，大迎角下细长体非对称涡控制与背风区原始涡系结构有关，其中包含对称涡系和非对称涡系。本文研究为大迎角下细长体非对称涡控制提供了一种新思路，同时也为丝状暴露电极DBD等离子体激励器的应用提供参考。

Abstract

Forebody vortex control with a novel wire-based DBD (Dielectric Barrier Discharge) plasma actuator is studied by wind tunnel experiments in the present work. The configuration of the wire-based DBD plasma actuator

including the material and diameter of the exposed electrode

is optimized through thrust measurements in quiescent air. The results show that the DBD plasma actuator with a wire-based exposed electrode made from tungsten has the highest thrust efficiency

and with the reduction of the diameter from

= 0.3 mm to

= 0.08 mm

the thrust efficiency can be greatly improved. The optimal configuration of

the wire-based DBD plasma actuator is used for the forebody vortex control through wind tunnel experiments. When the plasma control is not applied

results of the pressure and PIV measurements indicate that the flow field in the leeward zone is a distinct asymmetric vortex structure. Under plasma actuation

the asymmetric vortex structure can be symmetrical or even mirror asymmetric with respect to the case “plasma off”

and the control ability in the burst-mode actuation can be significantly improved compared to the steady operation. It is found that the forebody vortex control effect depends on the vortex structure of “plasma off”

which can be either symmetric or asymmetric. This study presents a new approach for the forebody vortex control with the wire-based DBD plasma actuator

which can further improve the aerodynamic flow control on aircrafts with slender bodies.

关键词

Keywords

references

KEENER E R, CHAPMAN G T. Similarity in vortex asymmetries over slender bodies and wings[J]. AIAA Journal, 1977, 15(9): 1370-1372. DOI:10.2514/3.60795

CAI J S, LUO S J, LIU F. Stability of symmetric and asymmetric vortices pairs over slender conical wing-body combinations[J]. AIAA Journal, 2006, 44(7): 1601-1608. DOI:10.2514/1.19677

BERNHARDT J E, WILLIAMS D R. Proportional control of asymmetric forebody vortices[J]. AIAA Journal, 1998, 36(11): 2087-2093. DOI:10.2514/2.310

MALCOLM G N. Forebody vortex control[J]. Progress in Aerospace Sciences, 1991, 28(3): 171-234. DOI:10.1016/0376-0421(91)90005-O

WILLIAMS D, WILLIAMS D. A review of forebody vortex control scenarios[C ] //28th Fluid Dynamics Conference, Snowmass Village, CO. Reston, Virginia: AIAA, 1997. doi: 10.2514/6.1997-1967

LIU F, LUO S J, GAO C, et al. Flow control over a conical forebody using duty-cycled plasma actuators[J]. AIAA Journal, 2008, 46(11): 2969-2973. DOI:10.2514/1.39435

LONG Y X, LI H X, MENG X S, et al. Flow control ov er a conical forebody using pulsed nanosecond discharge actuators[C ] //52nd Aerospace Sciences Meeting, National Harbor, Maryland. Reston, Virginia: AIAA, 2014. doi: 10.2514/6.2014-0933

LONG Y X, LI H X, MENG X S, et al. Influence of actuating position on asymmetric vortex control with nanosecond pulse DBD plasma actuators[J]. IEEE Transactions on Plasma Science, 2016, 44(11): 2785-2795. DOI:10.1109/TPS.2016.2583543

ZHENG B R, XUE M, KE X Z, et al. Unsteady vortex structure induced by a trielectrode sliding discharge plasma actuator[J]. AIAA Journal, 2018, 57(1): 467-471. DOI:10.2514/1.J057596

MENG X S, WANG J L, CAI J S, et al. Optimal DBD duty-cycle for conical forebody side-force proportional control[C ] . 51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Grapevine (Dallas/Ft. Worth Region), Texas. Reston, Virigina: AIAA, 2013. doi: 10.2514/6.2013-347

MORALEV I, SHERBAKOVA V, SELIVONIN I, et al. Effect of the discharge constriction in DBD plasma actuator on the laminar boundary layer[J]. International Journal of Heat and Mass Transfer, 2018, 116: 1326-1340. DOI:10.1016/j.ijheatmasstransfer.2017.09.121

HANSON R, LAVOIE P, BADE K, et al. Steady-state closed-loop control of bypass boundary layer transition using plasma actuators[C ] //50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee. Reston, Virginia: AIAA, 2012. doi: 10.2514/6.2012-1140

SERAUDIE A, VERMEERSCH O, ARNAL D. DBD Plasma actuator effect on a 2D model laminar boundary layer. Transition delay under ionic wind effect[C ] //29th AIAA Applied Aerodynamics Conference, Honolulu, Hawaii. Reston, Virginia: AIAA, 2011. doi: 10.2514/6.2011-3515

RIZZETTA D P, VISBAL M R. Large-eddy simulation of plasma-based turbulent boundary-layer separation control[J]. AIAA Journal, 2010, 48(12): 2793-2810. DOI:10.2514/1.J050014

HUANG X, ZHANG X. Streamwise and spanwise plasma actuators for flow-induced cavity noise control[J]. Physics of Fluids, 2008, 20(3): 037101. DOI:10.1063/1.2890448

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

KOZLOV A V, THOMAS F O. Plasma flow control of cylinders in a tandem configuration[J]. AIAA Journal, 2011, 49(10): 2183-2193. DOI:10.2514/1.J050976

Wang Yuling, Gao Chao, Wu Bin, et al. Simulation of Flow Around Cylinder Actuated by DBD Plasma[J]. Plasma Science and Technology, 2016, 18(7): 768-774.

ENLOE C L, MCLAUGHLIN T E, VANDYKEN R D, et al. Mechanisms and responses of a dielectric barrier plasma actuator: geometric effects[J]. AIAA Journal, 2004, 42(3): 595-604. DOI:10.2514/1.3884

HOSKINSON A R, HERSHKOWITZ N. Differences between dielectric barrier discharge plasma actuators with cylindrical and rectangular exposed electrodes[J]. Journal of Physics D: Applied Physics, 2010, 43(6): 065205. DOI:10.1088/0022-3727/43/6/065205

KOTSONIS M, GHAEMI S, VELDHUIS L, et al. Measurement of the body force field of plasma actuators[J]. Journal of Physics D: Applied Physics, 2011, 44(4): 045204. DOI:10.1088/0022-3727/44/4/045204

THOMAS F O, CORKE T C, IQBAL M, et al. Optimization of dielectric barrier discharge plasma actuators for active aerodynamic flow control[J]. AIAA Journal, 2009, 47(9): 2169-2178. DOI:10.2514/1.41588

ZHENG B R. Computational analysis of conical forebody at high angles of attack with transitional model[C ] //51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Grapevine (Dallas/Ft. Worth Region), Texas. Reston, Virigina: AIAA, 2013. doi: 10.2514/6.2013-991

CORKE T, POST M. Overview of plasma flow control: concepts, optimization, and applications[C ] //43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virginia: AIAA, 2005. doi: 10.2514/6.2005-563

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