CFD Analysis of NACA 0012 Aerofoil to Investigate the Effect of Increasing Angle of Attack on Coefficient of Lift and Coefficient of Drag
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Abstract
The significance of using proper blade design is increasing with advancements in aviation technology. Wings are used in a variety of applications, including aircraft, drones, wind turbines, and more. In this study, Ansys version 2021 is used to do a CFD analysis on a NACA 0012 to study the effect of increasing the angle of attack on the coefficient of lift. Analyses have been performed using Ansys Fluent. The k-w turbulence model was used to analyze geometry, designed in SOLIDWORKS. At a speed of 32 m/s, several angles of attack have been evaluated from 0° to 20° to investigate lift and drag coefficient. The results of this study were compared with the literature for validation. It has been observed that increasing the angle of attack will increase the lift coefficient initially but after a specific angle, flow separation takes place and the lift coefficient starts decreasing with a further increase in the angle of attack
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