| 圆柱／翼型干涉流场的试验研究 |
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| 引用本文： | 解克,李晓东,林大楷.圆柱／翼型干涉流场的试验研究[J].飞机设计,2009,29(4):6-12. |
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| 作者姓名： | 解克 李晓东 林大楷 |
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| 作者单位： | 北京航空航天大学,能源与动力工程学院,北京,100191 |
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| 基金项目： | 973课题，国家自然科学基金 |
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| 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.
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| 关 键 词： | 圆柱/翼型干涉 涡系 |
An Experimental Investigation of the Flow Field of Rod-airfoil Interaction |
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| XIE Ke,LI Xiao-dong,LIN Da-kai.An Experimental Investigation of the Flow Field of Rod-airfoil Interaction[J].Aircraft Design,2009,29(4):6-12. |
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| Authors: | XIE Ke LI Xiao-dong LIN Da-kai |
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| Institution: | School of Jet Propulsion;Beijing University Aeronautics and Astronautics;Beijing 100191;China |
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| Abstract: | 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 ex... |
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| Keywords: | PIV |
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