Abstract
An experimental investigation has been conducted on a two-dimensional NACA 0024 airfoil equipped with a leading-edgerotatingcylinder.Theairfoilwastestedfordifferentvaluesofleading-edgerotationsande apdee ection angles. The effects of the angle of attack ®, the cylinder surface velocity ratio Uc/U, and the e ap dee ection angle ± on lift and drag coefe cients, the size of the separated e ow region, and the stall angle of attack are included. The effect of Uc/U on the boundary-layer growth and turbulence intensity are also shown. Experimental results, for example, showed that the leading-edge rotating cylinder increases the lift coefe cient of a NACA 0024 airfoil from 0.85 at Uc/U = 0 to 1.63 at Uc/U = 4 and delays the stall angle of attack by about 160%. Smoke-wire e ow visualization results were also used to demonstrate the strong effect of the leading-edge rotating cylinder on the size of the recirculation region.
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