旋翼翼型动态失速非定常介质阻挡放电流动控制研究

李国强; 常智强; 张鑫; 马志明; 王畅; 易仕和

doi:10.7638/kqdlxxb-2023.0201

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旋翼翼型动态失速非定常介质阻挡放电流动控制研究

研究论文 | 更新时间：2026-05-28

- 旋翼翼型动态失速非定常介质阻挡放电流动控制研究
- Experimental investigation of dynamic stall control on a rotor airfoil using unsteady dielectric barrier discharge
- 空气动力学学报 2024年42卷第5期页码：64-71
- 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：
  
  李国强（1987—），男，安徽蚌埠人，研究方向：低速风洞试验，翼型动态试验技术. E-mail： CARDCL@126.com
  常智强*，研究方向：等离子体流动控制. E-mail： h14chang@163.com
- 基金信息：
  
  旋翼空气动力学重点实验室研究开放课题资助（RAL20200102-1）
- DOI：10.7638/kqdlxxb-2023.0201
  中图分类号： V211.73
- 纸质出版：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

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