Airfoil boundary layer separation and control at low Reynolds numbers

被引：11
|
作者：
Yarusevych, S
Sullivan, PE
Kawall, JG
机构：
[1] Univ Toronto, Dept Mech & Ind Engn, Toronto, ON M5S 3G8, Canada
[2] Ryerson Univ, Dept Mech & Ind Engn, Toronto, ON M5B 2K3, Canada
来源：
EXPERIMENTS IN FLUIDS | 2005年 / 38卷 / 04期
关键词：
D O I：
10.1007/s00348-005-0943-2
中图分类号：
TH [机械、仪表工业];
学科分类号：
0802 ;
摘要：
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.
引用
收藏
页码：545 / 547
页数：3
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