Experimental investigation of dynamic stall control on a rotor airfoil using unsteady dielectric barrier discharge

LI Guoqiang; CHANG Zhiqiang; ZHANG Xin; MA Zhiming; WANG Chang; YI Shihe

doi:10.7638/kqdlxxb-2023.0201

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Experimental investigation of dynamic stall control on a rotor airfoil using unsteady dielectric barrier discharge

更新时间：2026-05-28

- Experimental investigation of dynamic stall control on a rotor airfoil using unsteady dielectric barrier discharge
- Vol. 42, Issue 5, Pages: 64-71(2024)
- 作者机构：
  
  1. 国防科技大学空天科技学院,长沙,410073
  2. 中国空气动力研究与发展中心低速空气动力研究所,绵阳,621000
  3. 火箭军士官学校,潍坊,262500
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2023.0201
  CLC： V211.73
- Published：2024
- 稿件说明：
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李国强, 常智强, 张鑫, 等. 旋翼翼型动态失速非定常介质阻挡放电流动控制研究[J]. 空气动力学学报, 2024, 42(5): 64−71.

LI Guoqiang, CHANG Zhiqiang, ZHANG Xin, et al. Experimental investigation of dynamic stall control on a rotor airfoil using unsteady dielectric barrier discharge[J]. 2024, 42(5): 64-71.
李国强, 常智强, 张鑫, 等. 旋翼翼型动态失速非定常介质阻挡放电流动控制研究[J]. 空气动力学学报, 2024, 42(5): 64−71. DOI： 10.7638/kqdlxxb-2023.0201

LI Guoqiang, CHANG Zhiqiang, ZHANG Xin, et al. Experimental investigation of dynamic stall control on a rotor airfoil using unsteady dielectric barrier discharge[J]. 2024, 42(5): 64-71. DOI： 10.7638/kqdlxxb-2023.0201.

摘要

针对动态失速导致旋翼翼型气动性能恶化的问题，借助介质阻挡放电非对称构型激励器，通过脉动压力传感器测量，开展了旋翼翼型动态失速非定常等离子体流动控制研究。重点对非定常等离子体控制机理和非定常激励参数影响进行了探究，试验验证了非定常等离子体激励的良好控制能力。研究表明：非定常流动控制可以减弱翼型的升力骤降，20%的占空比就足以取得明显的控制效果；激励频率

= 1～2时的非定常控制效果最好，升力迟滞环面积减小16%，升力系数平均值提高6%。机理分析发现等离子体激励主要作用于动态失速涡脱落后，非定常激励明显削弱了动态失速涡脱落对翼型气动力的不利影响，同时非定常激励可以产生更多的涡以促进前缘逆压梯度的恢复和流动的重附着。

Abstract

To address the issue of rotor airfoil aerodynamic performance degradation due to dynamic stall

we conduct experimental investigations utilizing pulsating pressure sensors and asymmetric configuration actuators with dielectric barrier discharge. The focus is to investigate the unsteady plasma flow control on the rotor airfoil dynamic stall. Particularly

we aim to explore the underlying mechanism of unsteady plasma control and its sensitivity to actuation parameters. The experiments have confirmed the promising control capabilities of unsteady plasma actuation. The results indicate that the unsteady flow control can effectively mitigate

the sudden drop of airfoil lift

with a 20% duty cycle being sufficient to achieve significant control effects. A comprehensive parametric study on the dimensionless actuation frequency

demonstrates that the optimal performance of the unsteady control occurs at

= 1～2. This optimal condition yields a remarkable 16% reduction in the lift hysteresis loop area and a 6% increase in the average lift coefficient. Furthermore

by comparing the airfoil aerodynamic forces and pressure contours under steady and unsteady control modes

the control mechanism of the rotor airfoil dynamic stall based on the plasma actuation is analyzed. Notably

the plasma actuation primarily acts on the dynamic stall vortex shedding

while unsteady actuation significantly weakens the adverse effects of dynamic stall vortex shedding on the airfoil aerodynamic forces. Additionally

the unsteady actuation generates more vortices

thereby enhancing the recovery of the leading-edge reverse pressure gradient and the flow reattachment.

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references

王适存. 直升机空气动力学[M]. 南京: 南京航空航天大学, 1985: 57-68.

MCCROSKEY W J. The phenomenon of dynamic stall[R]. National Aeronuatics and Space Administration Moffett Field, CA, Ames Research Center, NASA-TM-81264 , 1981.

ZHAO Q J, JING S M, ZHAO G Q, et al . Review of research progress on dynamic stall mechanism and unsteady design of rotor airfoils[J ] . Acta Aerodynamica Sinica, 2021 , 39 ( 6 ): 70 − 84 (in Chinese).

HU S H, WEI B B . Experimental study on aerodynamic hysteresis of pitching airfoil under high Reynolds number[J ] . Experimental Technology and Management, 2023 , 40 ( 5 ): 100 − 104,115 (in Chinese).

CORKE T C, THOMAS F O . Dynamic stall in pitching airfoils: Aerodynamic damping and compressibility effects[J ] . Annual Review of Fluid Mechanics, 2015 , 47 : 479 − 505 .

HEINE B, MULLENERS K, JOUBERT G, et al . Dynamic stall control by passive disturbance generators[J ] . AIAA Journal, 2013 , 51 ( 9 ): 2086 − 2097 .

LEE B S, YE K, JOO W, et al. Passive control of dynamic stall via nose droop with gurney flap[C]//43rd AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada. Reston, Virigina: AIAA, 2005.

GERONTAKOS P, LEE T . Dynamic stall flow control via a trailing-edge flap[J ] . AIAA Journal, 2006 , 44 ( 3 ): 469 − 480 .

GERONTAKOS P, LEE T . PIV study of flow around unsteady airfoil with dynamic trailing-edge flap deflection[J ] . Experiments in Fluids, 2008 , 45 ( 6 ): 955 − 972 .

李爽. 风力机翼型动态失速的模型及流动控制机制研究[D]. 北京: 中国科学院大学, 2021.

VO H D. Control of rotating stall in axial compressors using plasma actuators[C]// 37th AIAA Fluid Dynamics Conference and Exhibit, Miami, Florida. Reston, Virginia: AIAA, 2007: 3845.

LI G Q, CHANG Z Q, ZHANG X, et al . Experiment on flow control of airfoil dynamic stall using plasma actuator[J ] . Acta Aeronautic a et Astronautica Sinica, 2018 , 39 ( 8 ): 122111 (in Chinese).

MUKHERJEE S, ROY S. Enhancement of lift and drag characteristics of an oscillating airfoil in deep dynamic stall using plasma actuation[C]//50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee. Reston, Virigina: AIAA, 2012.

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).

LI Y H, LIANG H, MA Q Y, et al . Experimental investigation on airfoil suction side flow separation by pulse plasma aerodynamic actuation[J ] . Acta Aeronautica et Astronautica Sinica, 2008 , 29 ( 6 ): 1429 − 1435 (in Chinese).

LI Y H, WU Y, ZHANG P, et al . Experimental investigation on airfoil stall separation suppression by plasma actuation[J ] . Acta Aerodynamica Sinica, 2008 , 26 ( 3 ): 372 − 377 (in Chinese).

WANG W B, HUANG Y, HUANG Z B, et al . PIV measurement of dielectric barrier discharge plasma flow control on NACA0015 airfoil[J ] . Journal of Experiments in Fluid Mechanics, 2012 , 26 ( 2 ): 1 − 5 (in Chinese).

POST M, CORKE T. Separation control using plasma actuators: Dynamic stall control on an oscillating airfoil[C]//2nd AIAA Flow Control Conference, Portland, Oregon. Reston, Virigina: AIAA, 2004: 1039-46.

MITSUO K, WATANABE S, ATOBE T, et al. Lift enhancement of a pitching airfoil in dynamic stall by DBD plasma actuators[C]//51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Grapevine (Dallas/Ft. Worth Region), Texas. Reston, Virigina: AIAA, 2013.

FRANKHOUSER M W, GREGORY J W. Nanosecond dielectric barrier discharge plasma actuator flow control of compressible dynamic stall[C]//46th AIAA Plasmadynamics and Lasers Conference, Dallas, TX. Reston, Virginia: AIAA, 2015.

GREENBLATT D, BEN-HARAV A, SCHULMAN M. Dynamic stall control on a vertical axis wind turbine using plasma actuators[C]//50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee. Reston, Virigina: AIAA, 2012.

WEAVER D, MCALISTER K W, TSO J . Control of VR-7 dynamic stall by strong steady blowing[J ] . Journal of Aircraft, 2004 , 41 ( 6 ): 1404 − 1413 .

ZHANG W G, SHI Z Y, LI G Q, et al . Numerical study on dynamic stall flow control for wind turbine airfoil using plasma actuator[J ] . Chinese Journal of Theoretical and Applied Mechanics, 2020 , 52 ( 6 ): 1678 − 1689 (in Chinese).

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