旋翼翼型动态失速等离子体流动控制试验研究  

Experimental Research on Dynamic Stalled Plasma Flow Control of Rotor Airfoil

作　　者：吴霖鑫 李国强[1,2] 杨永东[1,2] 张鑫[1,2] 陈磊[1,2] 赵光银 WU Linxin;LI Guoqiang;YANG Yongdong;ZHANG Xin;CHEN Lei;ZHAO Guangyin(Low Speed Aerodynamics Institute,China Aerodynamics Research&Development Center,Mianyang 621000,China;Key Laboratory of Rotor Aerodynamics,China Aerodynamics Research&Development Center,Mianyang 621000,China)

机构地区：[1]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 [2]中国空气动力研究与发展中心旋翼空气动力学重点实验室,绵阳621000

出　　处：《南京航空航天大学学报》2021年第5期801-812,共12页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：翼型动态失速是指机翼或叶片的当地迎角呈现周期或急剧变化时绕流附面层大范围分离带来的一种强烈的非线性、非定常流动现象。动态失速涡脱离翼型后缘流向下游时,会引发升力急剧下降、阻力迅速增大的失速和颤振问题。基于旋翼翼型两自由度动态试验装置和高频高速振荡试验装置,以典型旋翼翼型为研究对象,利用纳秒脉冲激励电源和介质阻挡放电等离子体激励器,在FL-11风洞和FL-20风洞开展了翼型动态失速等离子体流动控制试验研究,试验最高雷诺数突破1.7×10^(6),模型最高振荡频率突破10 Hz。试验结果表明,等离子体气动激励能够有效控制翼型动态失速,改善平均气动力,减小俯仰力矩负峰值,减小气动力/力矩随迎角变化的迟滞区域。Airfoil dynamic stall refers to a strong nonlinear and unsteady flow phenomenon caused by the large-scale separation of the surrounding surface layer when the local angle of attack of the wing or blade changes periodically or sharply.The dynamic stall vortex breaks away from the airfoil.When the trailing edge flows downstream,it will cause stall and flutter problems with a sharp drop in lift and a rapid increase in drag.Based on the two-degree-of-freedom dynamic test device of the rotor airfoil and the high-frequency and high-speed oscillation test device,the typical rotor airfoil is used as the research object,the experimental research on dynamic stall plasma flow control of airfoil is carried out in FL-11 and FL-20 wind tunnels by using nanosecond pulse excitation power supply and dielectric barrier discharge plasma exciter.The maximum Reynolds number in the test exceeds 1.7×10^(6),and the maximum oscillation frequency of the model exceeds 10 Hz.The test results show that the plasma aerodynamic excitation can effectively control the dynamic stall of the airfoil,improve the average aerodynamic force,reduce the negative peak of the pitching moment and the hysteresis area of the aerodynamic force/torque with the angle of attack.

关 键 词：旋翼翼型 动态失速 等离子体 耦合振荡 

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]