前缘吹气控制舵面流动分离  

Flow separation control on control surface by blowing from leading edge of control surface

作　　者：邓学蓥[1] 吴鹏[1] 王延奎[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191

出　　处：《北京航空航天大学学报》2012年第7期853-856,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：航空科学基金资助项目(2011ZA51003)

摘　　要：针对各种飞行器大舵偏下出现的流动分离问题,在北航D4风洞对旨在消除舵面流动分离的舵面前缘吹气技术进行了研究,为了降低控制分离所用的吹气量,吹气点设置在舵面前缘气流分离点处.应用粒子图像测速(PIV,Particle Image Velocimetry)技术,分析了舵面绕流在吹气量由小变大过程中所经历的3个不同演化阶段;由测压得到的舵面压力分布则显示,前缘吹气造成的引射作用使前缘吸力峰随吹气量增大而增大,这是前缘吹气能够使舵面升力增大的主要机理.实验结果还表明,前缘吹气可明显提高舵面升力,同时也可以显著降低舵面阻力.The wind tunnel experimental research on the flow separation control of control surface by blowing from leading edge of control was performed in D4 wind tunnel at Beihang University,in order to reduce the blowing air consumption.Blowing position was set at the separation point.The evolvement courses of flow field with the increasing of blowing momentum coeffecient was revealed by using particle image velocimetry（PIV） technique.The suction peak of control surface is increased as a result of ejector action which is caused by blowing,it is the main mechnisim of lift enhancement of leading edge blowing.The experiment results also indicate that not only the lift of control surface is enhanced,but also the drag is reduced.

关 键 词：吹气 分离控制 增升 机理 

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]