CFD simulation of NACA airfoilsat various angles of attack

Abstract

Abstract The need for more efficient design has become a main concern to work with a good range for angle of attack (AOA) to reduce the stall formation. In this project, two types of NACA series airfoils i.e., symmetrical and asymmetrical profiles depending on their usage in various sectors are compared. The profile of the airfoils is imported into ANSYS Fluent from the data files. The 2D geometry of the airfoils is simulated under two different wind velocitiesi.e., at 3m/s and 15m/s respectively. The graphs are plotted for comparing coefficients of lift (CL) and drag (CD)withrespect to the angle of attack(α) for symmetrical and asymmetrical airfoils. The stall formation with change of geometry and angle of attack is also observed.