Flow past an airfoil with a leading-edge rotation cylinder

被引：0

作者：

Du, X. ^{[1
]}

Lee, T. ^{[1
]}

Mokhtarian, F. ^{[2
]}

Kafyeke, F. ^{[2
]}

机构：

[1] Aerodynamics Laboratory, Dept. of Mechanical Eng., McGill University, Montreal, Que. H3A 2K6, Canada

[2] Advanced Aerodynamics, Bombardier Aerospace, Dorval, Que. H45 1Y9, Canada

来源：

Journal of Aircraft | 1600年 / 39卷 / 06期

关键词：

Aerodynamics - Anemometers - Boundary layers - Computer simulation - Drag - Flow measurement - Flow visualization - Lift - Pressure measurement - Rotation - Wakes - Wind tunnels;

D O I：

暂无

中图分类号：

学科分类号：

摘要：

The effects of leading-edge cylinder rotation on the boundary layer and wake, and lift-to-drag ratio of a NACA 0015 airfoil, were quantified. With cylinder rotation, a delayed boundary-layer flow separation accompanied by a narrowed wake and an enhanced lift could be obtained. As such, the boundary-layer momentum thickness decreased with increasing cylinder rotation and grew linearly with the stremwise distance along the airfoil surface. The given measurement not only demonstrate the improved aerodynamic performance through a leading-edge circulation control device, but also provide typical data for computer model validations.

引用

页码：1079 / 1084

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