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Effect of Angle of Attack on Coefficient of Lift of Naca Airfoil Blade Structure

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Document pages: 5 pages

Abstract: CFD simulations were conducted to estimate the effect of angle of attack on coefficient of lift of NACA 0012 airfoil blade structure. C grid unstructured mesh was generated in Gambit and imported to FLUENT. Simulation of flow field over NACA 0012 Airfoil was successfully completed for subsonic flow case with Mac number M=0.3 & angle of attack α=10 to 80 The simulated results indicate that the pressure on the lower surface of the airfoil increases while the pressure on the upper surface of the airfoil decreases as the angle of attack increases. The coefficient of lift was found to increase linearly as the angle of attack increases.

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