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Abstract Unsymmetrical airfoils are used to get a better lift-to-drag ratio. In this work, the overall performance of a NACA4412 unsymmetrical airfoil has been investigated through CFD simulations. The angle of attack is varied from 0° to 20° at the interval of 2°. The airflow velocity is kept constant at 30 m/s. From the investigation, it is observed that the optimum CL to CD ratio is obtained at an angle of attack of 5°. Beyond 5° AA, the CD rises rapidly. With an increase in AA, a backflow is observed near the trailing edge on the top half of the airfoil. The backflow becomes stronger with the increase in AA. The stagnation point also moves down towards the bottom surface from the tip of the airfoil with the increase in AA.
Ghose et al. (Thu,) studied this question.
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