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：
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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.
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页码：1079 / 1084
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