| 滑动放电等离子体控制细长体头部背风区非对称涡实验研究 |
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| 引用本文： | 金元中,郑博睿,喻明浩,刘园鹏,张倩,孙正中,于涛.滑动放电等离子体控制细长体头部背风区非对称涡实验研究[J].实验流体力学,2022,36(5):43-51. |
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| 作者姓名： | 金元中 郑博睿 喻明浩 刘园鹏 张倩 孙正中 于涛 |
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| 作者单位： | 1.西安理工大学，西安 710048 |
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| 基金项目： | 国家自然科学基金（51607188，61971345，12175177）；国防科技重点实验室基金项目（614220120030810） |
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| 摘 要： | 飞行器在大迎角飞行状态下，细长体头部背风区流场演变复杂，会出现非对称旋涡，产生随机侧向力，对飞行器的机动性和敏捷性影响很大。针对细长体大迎角非对称涡控制问题，采用顺流向布局的滑动放电等离子体激励器，结合测压和粒子图像测速（PIV）等手段，对细长体模型开展了风洞实验研究。研究结果表明:激励电压10 kV是流动控制开始生效的阈值电压；当来流速度10 m/s（雷诺数0.8×105）、迎角45°时（激励电压16 kV，归一化脉冲频率1.96），获得最佳流动控制效果，侧向力系数最高可降低83.48%；随着来流速度继续增大，流动控制效果逐渐减弱，预测在来流速度26 m/s时将完全失效。
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| 关 键 词： | 大迎角 非对称涡 粒子图像测速（PIV） 滑动放电 |
| 收稿时间： | 2021-08-23 |
Experimental study on flow control of asymmetric vortex over the leeward region of the head of the slender body by sliding discharge plasma actuation |
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| Affiliation: | 1.Xi’an University of Technology, Xi'an 710048, China2.City, University of London, London EC1V 0HB, UK3.The Green Aerotechnics Research Institute of Chongqing Jiaotong University, Chongqing 401135, China |
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| Abstract: | When the aircraft flies at a high angle of attack, the flow field on the leeward surface of the slender body evolves in a complicated manner, and asymmetric vortices appear, generating random lateral forces, which greatly affect the maneuverability and agility of the aircraft. In order to solve this problem, a sliding discharge plasma actuator with an along-stream layout was used to conduct wind tunnel experiments on a slender body model, combined with pressure measurement and particle image velocimetry（PIV）. The experimental results show that the actuation voltage of 10 kV is the threshold voltage at which the flow control starts to take effect. When the velocity of the incoming flow is 10 m/s（Re=0.8×105）, the angle of attack is 45°, and the actuation voltage is 16 kV, the best flow control effect can be achieved at the normalized pulse frequency of 1.96, the lateral force coefficient can be reduced by 83.48%. However, as the flow velocity increases, the flow control effect becomes weaker gradually and is expected to disappear at 26 m/s. |
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