基于压力反馈的等离子体主动流动控制试验  

Experiment of the plasma active flow control based on pressure feedback

作　　者：牛中国[1] 刘捷[1] 胡秋琦 梁华[3] NIU Zhongguo;LIU Jie;HU Qiuqi;LIANG Hua(Low Speed and High Reynolds Aeronautics Laboratory,Aerodynamics Research Institute,Aviation Industry Corporation of China,Limited,Harbin 150001,China;Education Center of Experiments and Innovations,Harbin Institute of Technology(Shenzhen),Shenzhen Guangdong 518000,China;Aeronautics and Astronautics Engineering College,Air Force Engineering University,Xi’an 710038,China)

机构地区：[1]中国航空工业空气动力研究院低速高雷诺数航空重点实验室,哈尔滨150001 [2]哈尔滨工业大学(深圳)实践与创新实践教育中心,广东深圳518000 [3]空军工程大学航空航天工程学院,西安710038

出　　处：《航空动力学报》2024年第3期69-76,共8页Journal of Aerospace Power

摘　　要：基于翼面压力分布与流动分离的对应关系,提出了一种用于等离子体激励抑制翼面流动分离的反馈控制方法,该方法通过模型表面特征点的压力判断流动分离情况,根据判断结果自动施加或取消等离子体控制。在NACA0015翼型和飞翼布局模型上分别对该方法进行了风洞试验验证,试验表明:基于压力反馈的等离子体流动控制方法能够实现对翼面流动分离的主动控制,通过控制能够改善模型的失速特性;在飞翼布局模型上,等离子体压力反馈控制与开环控制的效果基本一致,在来流风速为30 m/s时反馈控制与开环控制均能使模型的最大升力系数提高27%以上、失速迎角推迟4°。Based on the corresponding relationship between the wing pressure distribution and flow separation,a feedback control method for separation flow control by plasma was proposed.Using this method,the separation of wing surface can be distinguished by the pressure of the characteristic points on the model surface,and the plasma flow control can be automatically applied or canceled according to the judgment results.The method was verified on NACA0015 airfoil and flying wing layout models respectively in wind tunnel experiment.The experiment showed that the plasma flow control method based on pressure feedback can realize the automatic suppression of the wing flow separation,thus improving the stall characteristics of the model.The effect of the plasma based on pressure feedback was consistent with that of open-loop control.Both of them can increase the maximum lift coefficient of the flying wing layout model by more than 27%and the stall angle of attack by 4°at a wind speed of 30 m/s.

关 键 词：流动控制 等离子体 流动分离 反馈控制 风洞试验 

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]