圆柱/翼型干涉流场的试验研究  

An Experimental Investigation of the Flow Field of Rod-airfoil Interaction

作　　者：解克[1] 李晓东[1] 林大楷[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《飞机设计》2009年第4期6-12,共7页Aircraft Design

基　　金：973课题(No.2007CB714604);国家自然科学基金(No.50676003)资助项目

摘　　要：在风洞出口低速流中,以NACA0012尾缘钝化翼型为模型,利用粒子成像测速系统,研究了圆柱/翼型结构干涉流动时翼型前缘、近壁和尾缘区域的流场。试验结果表明,由于上游圆柱引起的卡门涡街和翼型相互干涉,在翼型前缘存在大尺度涡的变形、拉伸和破裂,在翼型表面近壁区域和尾迹流场中仅存在小尺度湍流涡,由此可以推断翼型前缘可能是干涉噪声的主要声源区。A Particle Image Velocimeter（PIV） technique is utilized to measure the flow field of rod airfoil interaction in the region of the leading edge, near wall surface and trailing edge of a NACA0012 airfoil with blunted trailing edge in an open low - speed wind tunnel. Experiment results show that the vortex shedding from the upstream rod impinges on the lead edge of the airfoil. Large scale vortex deformation, stretching and splitting occur at the leading edge of the airfoil and only small scale turbulence vortices exist around the airfoil wall and wake. It can be inferred that the airfoil leading edge is possibly the dominant noise source of rod - airfoil interaction.

关 键 词：圆柱/翼型干涉 涡系 PIV 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]