涡流发生器布局方式对翼型失速流动控制效果影响的实验研究  

Experimentally Studying Effects of Different Layouts of Vortex Generator on Controlling Stall Flow over Airfoil

作　　者：郝礼书[1] 乔志德[1] 宋文萍[1] 

机构地区：[1]西北工业大学翼型叶栅空气动力学国家重点实验室,陕西西安710072

出　　处：《西北工业大学学报》2011年第4期524-528,共5页Journal of Northwestern Polytechnical University

基　　金：国家高技术研究发展计划(2007AA05Z448)资助

摘　　要：采用风洞实验的方法开展了涡流发生器布局方式对翼型失速流动控制效果影响的研究。通过对比在干净翼和安装涡流发生器情形下的气动力,重点讨论了涡流发生器布局方式对翼型失速流动控制的影响。结果表明:第一类和第二类布局方式都能够有效抑制翼型失速,提高最大升力系数,其失速特性得到极大改善;第二类布局方式对失速的控制效果略优于第一类,同时涡流发生器方向角越小控制效果越好;第三类布局方式对失速流动控制几乎没有效果,最大升力有所下降,同时伴随阻力的大幅增加。The introduction of the full paper discusses briefly past relevant research and then proposes the research mentioned in the title. Sections 1 and 2 present our research and its evaluation. Section 1 explains how we did our experiments; Tables 1, 2, and 3 present respectively the details of layout No. 1, layout No. 2, and layout No. 3 of vortex generator. The core of section 2 consists of ： （ 1 ） the stall flow over airfoil is suppressed evidently by the first two layouts; （2） the maximum lift coefficient is increased dramatically for the first two layouts; （3） the control effect of stall flow over airfoil for layout No. 2 is much better than that for layout No. 1 ; （4） for both layout No. 1 and layout No. 2, the inclined angle of the vortex generator is smaller and the control effect of stall flow over airfoil is better; （5） layout No. 3 of vortex generator is almost of no use for suppressing the stall flow over airfoil; the maximum lift coefficient is decreased slightly, and the drag is increased markedly.

关 键 词：涡流发生器 翼型 布局方式 失速特性 流动控制 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程]