翼型极大迎角风洞试验技术研究  

Research on wind tunnel test technique for airfoil at very high angle of attack

作　　者：焦予秦[1] 王龙[1] 高永卫[1] 肖春生[1] 

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

出　　处：《实验流体力学》2013年第4期102-108,共7页Journal of Experiments in Fluid Mechanics

基　　金：国家高技术研究发展计划(863计划)(SS2012AA051301)

摘　　要：在NF-3风洞的二元试验段开展了翼型极大迎角(±180°)条件下气动特性的试验技术研究。针对翼型极大迎角风洞试验的洞壁干扰,提出了风洞壁压信息洞壁干扰修正的改进方法。试验结果表明,发展的试验技术和提出的洞壁干扰修正方法适合于翼型极大迎角试验。The research on test technique of aerodynamic characteristics of wind turbine airfoil at high angle of attack is carried out in the two-dimensional test section of NF-3low speed wind tunnel in the Northwestern Polytechnical University.For the wall interference for airfoil wind tunnel test at very high angle of attack from-180°to＋180°,the improved wall pressure message method（IWPMM）for wall interference correction of airfoil wind tunnel test is put forward.It is shown from test results that the airfoil test technique developed in this paper and the wall interference correction method put forward are fit to airfoil test at very high angle of attack.

关 键 词：风洞试验 翼型 极大迎角 洞壁干扰 壁压信息法 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]