Study of NACA 6212 Airfoil and Investigation of its Aerodynamic Properties in Different Angles of Attack

Abstract

One of the most important topics in aerodynamics is the study of different types of airfoils. Airfoils produce different aerodynamic forces depending on the thickness distribution, the radius of the attacking edge, the thickness of the escape edge, the ratio of chord length to maximum thickness, curvature, and other parameters. Understanding the aerodynamic properties of airfoils in different conditions allows engineers to select the optimal mode in designing and construction. Studies on NACA 6212 have been limited, so the purpose of this study was to study this airfoil. For this purpose, the numerical solution method was used and the aerodynamic properties of this airfoil in different attack angles between –20 to +20 degrees were investigated in Mach number equal to 0.5. The results show that in the angle of positive attacks, the flow lines above the surface of the airfoil are close to each other and are more compact, and the absolute value of the pressure coefficient in this part is the highest but for the angle of negative attacks, the situation is quite opposite. The results showed that in general, by increasing the angle of attack, the amount of drag coefficient and the absolute value of the pressure coefficient increases. For positive attack angles, the lift coefficient increases with increasing attack angle but for negative attack angles, the lift coefficient decreases with increasing attack angle. Finally, the validity of the research results was examined and compared with previous studies which showed that the results of this research have a 9% error. This amount of error is acceptable and is due to some minor differences in the simulation method.