Effect of leading-edge roughness on boundary layer transition of an oscillating airfoil
Effect of leading-edge roughness on boundary layer transition of an oscillating airfoil
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DOI：
10.1016/j.scient.2012.12.035
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发表时间：
2013-06
期刊：
影响因子：
1.4
通讯作者：
F. R. Marzabadi;M. Soltani
中科院分区：
文献类型：
--
作者：
F. R. Marzabadi;M. Soltani
使用多个热膜传感器进行了一系列实验，研究前沿粗糙度对风力涡轮机叶片截面边界层状态的影响。实验涉及静态和动态测试，其中机翼运动为切入式振荡。表面砂粒粗糙度的应用模拟了风力涡轮机叶片上出现的表面不规则性。测量结果表明，增加攻角会导致过渡位置向前缘移动。表面粗糙度将过渡点移向前缘，并导致后缘早期湍流分离，从而导致翼型效率降低。边界层不稳定频率在转变过程中占主导地位。
A series of experiments were conducted to study the effect of leading-edge roughness on the state of the boundary layer of a wind turbine blade section using multiple hot-film sensors. The experiments involved static and dynamic tests, where airfoil motion was of plunging type oscillation. The application of surface grit roughness simulates surface irregularities that occur on the wind turbine blades.The measurements showed that increasing the angle of attack results in movement of transition locations toward the leading edge. Surface roughness moved the transition point toward the leading edge and caused early trailing edge turbulent separation, which resulted in reducing the effectiveness of the airfoil. Boundary layer instability frequencies were dominated through the transition.