Airfoil boundary layer separation and control at low Reynolds numbers
Airfoil boundary layer separation and control at low Reynolds numbers
复制标题
低雷诺数下的翼型边界层分离和控制
DOI：
10.1007/s00348-005-0943-2
复制
发表时间：
2005
影响因子：
2.4
通讯作者：
J. Kawall
中科院分区：
文献类型：
--
作者：
S. Yarusevych;P. Sullivan;J. Kawall
采用热线风速仪和表面压力测量方法对NACA0025翼型的边界层分离进行了实验研究。结果提供了额外的洞察周期性边界层控制，这表明，匹配的激励频率与最放大的干扰分离剪切层是最佳的，以提高翼型性能。
The boundary layer separation on a NACA 0025 airfoil was studied experimentally via hot-wire anemometry and surface pressure measurements. The results provide added insight into periodic boundary layer control, suggesting that matching the excitation frequency with the most amplified disturbance in the separated shear layer is optimal for improving airfoil performance.