Numerical Study of Rotating Cylinder Effects on the Performance of a Symmetrical Airfoil Section
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Numerical studies of a NACA 0024 airfoil section with a leading edge rotating cylinder are made using ANSYS CFX 14. Three different turbulence models, SST k-ω, Standard k-ω and k-ε were utilized to investigate the flow field of the airfoil section. The lift, drag and lift to drag ratios are obtained for each turbulence model. The time dependent simulations gave the mean values of lift and drag coefficients in addition to the pressure distributions and the velocity profiles on the airfoil surfaces. The lift increased approximately 77% and the stall angle increased from 10 to 18 degrees with the use of a rotating cylinder. This is a proof that the rotating cylinder had a desirable effect on the performance of this airfoil section.
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