Effect of Suction Holes on the Aerodynamic Performance of NACA 0012 Airfoil

The performance of airfoils, such as the NACA 0012, is critical in aerodynamic applications, with lift and drag forces being key factors. However, flow separation at higher angles of attack limits the efficiency of airfoils, leading to stall and a sharp decrease in performance. Suction holes have been proposed as a method to control boundary layer behavior and delay flow separation, but their effect on lift-to-drag (CL/CD) ratios and stall angles remains inadequately explored. This research seeks to address the gap by analyzing the influence of suction holes on the aerodynamic performance of the NACA 0012 airfoil. Using a wind tunnel experiment across angles of attack ranging from −20° to 20° and frequencies of 5 Hz, 10 Hz, and 15 Hz, the study aims to determine the changes in boundary layer behavior, identify the stall angle, and compare the CL/CD ratios of the NACA 0012 with and without suction holes. The results indicate that the addition of suction holes significantly improves the aerodynamic performance by increasing the magnitude of the lift coefficient, reducing drag, and enhancing the overall lift-to-drag ratio.