Abstract: Nowadays, developing aviation jet engines are the main driving force for transport vehicles. The study on electric propulsion concepts with distributed propellers and distributed duct fans for the transport vehicles has already begun, and the new propulsion is the core competence of future transport aviation aircraft. In this paper, the actuator disk method is used to verify individual propeller firstly, and the calculated thrust and torque agree well with the test results. Then, based on Reynolds averaged N-S equations and combined with the SA turbulence model, the wing slipstream effects on of distributed propellers with different rotating directions under the condition of low speed and high thrust at low altitude are analyzed by replacing the distributed propellers with actuator disk. Finally, the wing slipstream effects of single propeller with positive and negative rotating directions are studied, especially the effects on the lift and drag. The results show that the lift and drag of the aircraft with slipstream effects are both greater than those without slipstream effects for four types of distributed propeller rotating direction. The lift is closely related to the number of suction peaks on the upper and lower surfaces, and the types of distributed propeller rotating direction directly determine the number of wing suction peaks, especially the wing tip rotating direction. When adjacent blades rotate in the opposite directions, the blades in the middle position of the rotation shaft are both in the upward and downward states, leading to strengthened or weakened wing suction of the leading edge in the middle position compared with that in the same rotating direction. Moreover, as the wingtip propeller rotates in the direction opposite to the wingtip vortex rotating, the lift increases and the drag decreases.