Abstract
The Numerical analysis of a NACA 0024 airfoil with rotating cylinders as moving surfaces is performed using unsteady Shear Stress Transport SST turbulence model in ANSYS CFX 14. The effects of the leading edge rotating cylinder with approximately 30% of the surface area exposed to the free stream velocity are investigated and compared with experimental data available in the open literature. The airfoil investigated has a chord length of C = 0.2 m and Re of the flow = 6.6 × 10^4. The numerical analysis of the airfoil with a 30° flap angle is presented and compared first with an airfoil with one leading edge rotating cylinder and also with an airfoil having two rotating cylinders. The results show that the corresponding lift coefficient and the lift to drag ratios were increased significantly due to the contribution of the rotating cylinders in addition to the flap. For example, the lift coefficient of the airfoil with a flap angle of δ = 30° is increased approximately by 45% with the use of two rotating cylinders and the stall angle is increased from α =10° to 19° (90%).
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