In order to investigate the performance of airfoils caused by boundary layer separation, this paper studies the performance using pressure coefficient simulated in ANSYS, SOLIDWORK and validated with an open cycle subsonic wind tunnel experiment. The problem is the possible lack of equipment to simulate and validate the action of aerodynamic and aeroelastic behavior due to the wind effect. In this project, the objective is focused on the pressure coefficient on a NACA 2412 airfoil of chord 16 and span 12, which was experimentally determined at Reynolds of 0.165 x 106, over angles of attack from -5° to 15°. It resulted in a simulation of the pressure coefficient, where by varying the angle of attack from -5° to 15°, the suction continuously increases at the leading edge of the top surface so that the pressure coefficient gradually decreases. It was concluded that when validating the results between ANSYS and T.V.EPN, an error of 21% was obtained, as opposed to Fluent Solidwork, which has an error of 55%.