The airport surface effect on aerodynamic characteristics of an airfoil NACA 0012 at different height was investigated. The lift, drag and moment coefficients are numerically calculated using singularity method for Mach number M = 0.3 and different angles of attack. The runway surface was represented by the wind tunnel wall and the wall distance control (h/c) from the wing. This paper showed that this airfoil, in order to work with good aerodynamic characteristics in take-off and landing, must be at height h/c <0.75 and fixed at an angle more than 0o with the center line of aircraft body. At height (h/c >0.75), the action of the wing is inverted, so negative forces are generated for all angles of attack. There is good agreement in this paper with the work of other researchers.