加装涡流发生器S形进气道迎角特性数值研究  

Numerical investigation of s-shaped inlet performance at different angle of attack with and without vortex generators

作　　者：李大伟[1] 马东立[2] 

机构地区：[1]北京航空航天大学无人驾驶飞行器设计研究所,北京100191 [2]北京航空航天大学航空学科与工程学院,北京100191

出　　处：《哈尔滨工业大学学报》2013年第5期114-118,共5页Journal of Harbin Institute of Technology

摘　　要：为了研究加装涡流发生器后S形进气道在不同来流迎角下的内流特性,利用CFD方法对加装涡流发生器前后的S形进气道迎角特性进行了数值仿真,首先通过在已有的S形进气道内部安装涡流发生器来改善出口流场分布,给出了涡流发生器的设计参数,包括导流叶片的高度、弦长、攻角和安装站位(轴向站位和横向站位),其次,分析了不同迎角下,加装涡流发生器前后S形进气道内流特性的变化.分析结果表明,在正负10°迎角范围内,加装涡流发生器都能够改善S形进气道出口流场品质,周向畸变指数平均下降0.1,但对出口总压恢复系数没有改善.在大迎角情况下,由于进口气流产生分离,涡流发生器已无法对来流进行有效的导向作用,从而导致出口流场变得异常紊乱,周向畸变指数陡增.这些分析结果对涡流发生器的设计有一定的指导意义.The essence of this paper is to report the computational research in a S-shaped inlet performance at different angle of attack with and without vortex generators.First,several vortex generators were set near the entry of diffuser to effectively reduce flow distortion produced in the S-shaped inlet.Several parameters,i.e.the ratio of generator blade height to local boundary layer thickness,the locating position,and the angle against centerline have been given.Second,the performance of the S-shaped inlet with and without vortex generators at different angle of attack was developed by using a computational fluid dynamics(CFD) procedure.The results show that in the ±10°angle of attack range,by using a properly designed vortex generator the total pressure circumferential distortion can be greatly reduced about 0.1 and the flow quality can be improved,but the total pressure recovery couldn't be raised.At high angle of attack,because of flow separations,the effect of the vortex generator was reduced.These results should provide valuable guidance in designing vortex generator installations in the S-shaped inlet.

关 键 词：S形进气道 流场控制 涡流发生器 迎角特性 

分 类 号：V228.7[航空宇航科学与技术—飞行器设计]