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  

Experimental study on flow control of asymmetric vortex over the leeward region of the head of the slender body by sliding discharge plasma actuation

作　　者：金元中 郑博睿 喻明浩 刘园鹏 张倩[1] 孙正中 于涛 JIN Yuanzhong;ZHENG Borui;YU Minghao;LIU Yuanpeng;ZHANG Qian;SUN Zhengzhong;YU Tao(Xi’an University of Technology,Xi'an 710048,China;City,University of London,London EC1V 0HB,UK;The Green Aerotechnics Research Institute of Chongqing Jiaotong University,Chongqing 401135,China)

机构地区：[1]西安理工大学,西安710048 [2]伦敦大学城市学院,伦敦EC1V 0HB [3]重庆交通大学绿色航空技术研究院,重庆401135

出　　处：《实验流体力学》2022年第5期43-51,共9页Journal of Experiments in Fluid Mechanics

基　　金：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)。

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。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 k V 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.

关 键 词：大迎角 非对称涡 粒子图像测速(PIV) 滑动放电 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]