Experimental Investigations on Aerodynamic Performances of NACA0012 Airfoil

Abstract

The aerodynamic characteristics for the various angles of attack at different Reynolds numbers with a view to extending the knowledge of the pressure distribution over the NACA 0012 airfoil have been measured in a low-speed subsonic wind tunnel. Experiments were carried out by varying the angle of attack from −30 to +30 degrees and the velocity varied from 10 m/s to 25 m/s. The lift coefficient and drag coefficient for the NACA 0012 airfoil are obtained by measuring the pressure distribution from the pressure ports situated over the airfoil surface.