CFD Analysis of NACA 0012 Aerofoil to Investigate the Effect of Increasing Angle of Attack on Coefficient of Lift and Coefficient of Drag

1Citations
Citations of this article
45Readers
Mendeley users who have this article in their library.

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.

Cite

CITATION STYLE

APA

Khalid, M. H. (2022). CFD Analysis of NACA 0012 Aerofoil to Investigate the Effect of Increasing Angle of Attack on Coefficient of Lift and Coefficient of Drag. Journal of Studies in Science and Engineering, 2(1), 74–86. https://doi.org/10.53898/josse2022216

Register to see more suggestions

Mendeley helps you to discover research relevant for your work.

Already have an account?

Save time finding and organizing research with Mendeley

Sign up for free