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Numerical Analysis of Boundary Layer Separation Control
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DOI: https://doi.org/10.15866/ireme.v9i1.4490
Abstract
The flow field of a NACA 0024 airfoil is investigated using ANSYS CFX 14. The airfoil used is equipped with a rotating cylinder mounted at its leading edge. Shear Stress Transport (SST) k-ω turbulence model is used in accordance with time dependent simulations. The numerical results are compared with published experimental data. The mean lift coefficient, the pressure coefficient and the velocity profiles at different sections of the airfoil surface are obtained and compared with Experimental results. Both cases of rotation and no rotation of the cylinder are presented. The maximum lift coefficient as well as the stall angle is increased when the cylinder rotation is present. The numerical data of lift coefficient values compared well with the experimental data.
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