The mathematical model of plasma flow control on airfoil was established by solving a two-dimensional fluid model of surface discharge.The body force induced by the plasma aerodynamic actuation was obtained.The momentum and thermal energy were added to the Navier-Stokes equation as source terms.Simulation investigation of plasma flow control on NACA0009 airfoil stall separation suppression was performed under low Reynolds number conditions.The influence of the intensity of the plasma aerodynamic actuation as well as the electrode number and position was investigated.The lift coefficient increased from 0.7449 to 1.2404 and the drag coefficient reduced from 0.4012 to 0.3503 after actuation in the case of Re=58000 at an angle of attack of 24°.