In this paper, a numerical study of aerodynamic characteristics using CFD method of the two dimensional flow around NACA 0012 and NACA 4412 airfoils at various angles of attack from -100 to 250, and operating at Re 170000 is presented. The formation of flow patterns, pressure distribution, pressure coefficient (Cp), lift coefficient (Cl), drag coefficient (Cd), moment coefficient (Cm), Skin friction coefficient distribution along the chord. The Y+ wall value curve as a validation that the mesh formation is in accordance with the requirements, i.e.: Y+ wall value below 10 for viscous dominate flows and for SST turbulent model viscous. The geometry of NACA 0012 and NACA 4412 airfoils are created using SolidWorks, CFD analysis is carried out using Ansys Workbench 2018. The results show that the stall condition at NACA 0012 is at an angle of attack of 150, while at NACA 4412 it is at 160. Under the stall conditions, Cl of NACA 4412 is approximately 13 percent higher than NACA 0012, while the value of Cd shows almost the same value for both NACA 0012 and NACA 4412.