: In this research, we want to investigate interaction of propeller on wing. We do this work in potential environment to use its equations and reduce solution costs. In this way we model the three dimensional wing by distribution of source and doublet. We suppose effects of propeller and its revolution as a input velocity profile for wing. We can find this distribution from different theories. But for having steady state answers and so to model swirl velocity of behind propeller, we use the momentum theory that is one of the actuator disk models. At first, we test the wing with off motor propeller that shows, code results have very good agreement with experiment. We can find such these results in total lift coefficient and total drag coefficient versus angle of attack diagrams and local lift coefficient versus span of wing. After turning on the motor propeller, swirl and axial velocities due it as input velocity to wing add to fluid velocity at infinity and finally appear in equations as zero flow normal to the surface boundary condition. Total lift coefficient versus angle of attack that is acquired from this state, have a good agreement with experiment. So local lift coefficient follows experimental diagrams.