基于后缘小翼的翼型动态失速主动控制试验  

Test on active control of airfoil dynamic stall based on trailing edge flap

作　　者：李国强 宋奎辉[2] 覃晨 赵光银 吴霖鑫 杨永东 LI Guoqiang;SONG Kuihui;QIN Chen;ZHAO Guangyin;WU Linxin;YANG Yongdong(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;Low Speed Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China)

机构地区：[1]国防科技大学空天科学学院,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

出　　处：《航空学报》2024年第3期105-120,共16页Acta Aeronautica et Astronautica Sinica

基　　金：预研共用技术项目(50906030601);预研综合研究项目(JK20211A020092)。

摘　　要：针对旋翼动态失速导致的非定常载荷增加和失速颤振问题,开展了基于后缘小翼的翼型动态失速主动控制试验,试验雷诺数Re=7.0×10^(5),减缩频率k=0.097。采用动态压力测试手段,重点分析了后缘小翼不同振荡相位差、幅值、平衡迎角对翼型动态失速的影响规律。结果表明,后缘小翼能以振荡周期T的1/2为时间间隔,周期交替地改变翼型的气动性能,在后缘小翼与翼型振荡相位差为0°的条件下,实现了俯仰力矩峰值降低54.9%的控制效果,同时更大的后缘小翼振荡幅值能实现更好的非定常载荷控制效果,但过大的振荡幅值有可能导致失速颤振。后缘小翼振荡平衡迎角的引入能起到调节升力系数、气动阻尼的作用。Aiming at the increase of unsteady load and stall flutter caused by dynamic stall,test research focusing on the control of airfoil dynamic was carried out using an airfoil test model with trailing edge flaps.The test Reynolds num⁃ber was Re=7.0×10^(5),and the reduced frequency k=0.097.Dynamic pressure measurement was used to analyze the influence of different oscillating phase offsets,amplitudes and equilibrium angles of attack of the trailing edge flap on the airfoil during dynamic stall.The results show that the trailing edge flap with continuous sinusoidal oscillation can alternately change the aerodynamic performance of the airfoil with the time interval of 1/2 of the oscillation period.When the phase offset between the trailing edge flap and airfoil model is 0°,the peak pitching moment can reduce by 54.9%and a larger oscillation amplitude of the trailing edge flap seems to achieve a better control effect of unsteady load,but stall flutter may appear when it is too large.The oscillation equilibrium angle of attack of the trailing edge flap can change the lift coefficient and aerodynamic damping.

关 键 词：后缘小翼 动态失速 失速颤振 气动阻尼 旋翼 

分 类 号：V211.79[航空宇航科学与技术—航空宇航推进理论与工程]