In the applied aerodynamics field, analysis ofthe wind turbine blades aerodynamics specifications used to use theirs aerodynamic equations. However, the governing equations of the behaviours of an airfoil in the wind flow are difficult to find down their solutions, even impossible in some cases. In this paper, an aerodynamic of NACA 4-digit airfoil model, which is based on the panel method is developed. Applied the aerodynamic model, an algorithm and computer program using Matlab is developed. Using the program, the pressure distribiutions, lift and drag coefficients of the airfoil are determined also. These results are compared with some academic computational software in aerodynamic to verify the model and the program, which are developed also.