Boundary Layer Separation and Control at Low Reynolds Numbers

机译：低雷诺数的边界层分离和控制

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Laminar boundary layer separation occurs on the upper surface of the NACA 0025 airfoil for Re_c=15x10~4 and Re_c=10x10~4 and at angles of attack of 0°, 5° and 10°. The present findings establish that the optimum excitation frequency reported in matches that of the most amplified disturbance in the separated shear layer for a given Reynolds number and angle of attack. Exciting the boundary layer at that frequency promotes separated shear layer transition, bringing about its reattachment and the formation of a separation bubble.

机译：当Re_c = 15x10〜4和Re_c = 10x10〜4且迎角为0°，5°和10°时，层边界层分离发生在NACA 0025机翼的上表面。目前的发现表明，对于给定的雷诺数和迎角，报道的最佳激发频率与分离的剪切层中最大的扰动相匹配。以该频率激发边界层会促进分离的剪切层过渡，从而使其重新附着并形成分离气泡。

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来源
《Canadian Congress of Applied Mechanics(CANCAM 2005); 20050530-0602; Montreal(CA)》|2005年|P.247-248|共2页
会议地点 Montreal(CA)
作者
S. Yarusevych; J.G. Kawall; P.E. Sullivan;
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作者单位

Department of Mechanical and Industrial Engineering, University of Toronto, Toronto, Ontario, Canada, M5S 3G8;

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原文格式 PDF
正文语种 eng
中图分类机械制造工艺;
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Boundary Layer Separation and Control at Low Reynolds Numbers

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