等离子体激励用于两段翼型增升的试验研究  

Test research of two-element airfoil lift enhancement by plasma actuator

作　　者：王万波[1,2] 章荣平[1,2] 黄宗波[2] 黄勇[1,2] 王勋年[1,2] 沈志洪[2] 张鑫[2] 

机构地区：[1]空气动力学国家重点实验室,四川绵阳621000 [2]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2013年第1期64-68,共5页Acta Aerodynamica Sinica

基　　金：空气动力学国家重点实验室基金资助(SKLA2010A2502)

摘　　要：在NACA23018两段翼型上安装等离子体激励器,通过风洞测力和丝线流态试验,研究了等离子体对翼型最大升力和失速迎角的影响。研究表明,等离子体激励可以显著地增加NACA23018两段翼型的最大升力系数和失速迎角,来流风速20m/s时,最大升力系数增加52%,失速迎角增加12.4°。等离子体激励和前缘缝翼的作用类似,并且可以和后缘增升装置配合使用,在运输类飞机设计中有潜在的应用前景。The effect of plasma actuator on the maximum lift and stall angle of NACA23018 two-element airfoil was studied in the wind tunnel. The force test and flow visualization results show that the plasma ac- tuator can efficiently increase the maximum lift and stall angle. The maximum lift coefficient increases 52% and stall angle increases 12.4%at free-stream velocity of 20m/s. Plasma actuator has the same function as leading edge slat, and it can be used with other trailing edge high-lift system, so it has a potential application foreground in the design of transport aircraft.

关 键 词：等离子体 两段翼型 风洞试验 增升 

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]