The slipstream produced by the propeller airplane will significantly interfere with the swept components. The study of the effect of the tail wing on the slipstream will help to decouple the slipstream and tail wing disturbances. The dynamic overlapping grid method is used to simulate the rotation of the propeller fixed axis. By solving the three-dimensional Unsteady Reynolds Average Navier-Stokes(URANS) equations, the state of a propeller airplane with tail wing with/without slipstream is simulated numerically. The correctness of the calculation method is verified by the experimental results. On this basis, calculations of the slipstream of the configuration with/without tail wing are carried out. The results show that the lift and drag aerodynamics variation law are almost the same after deducting of the aerodynamic force of the tail wing. The pitching moment is different due to the modification of the fuselage rear body. By comparing the slice velocity distribution clouds of the configurations with/without tail wing, variation curves of the down wash angle and the side wash angle at different spatial positions and with different thrust coefficients, it is found that the effect of the tail wing on the slipstream is only limited to the surroundings, and the rules of disturbance of the tail wing with different thrust coefficients are also very similar. Based on the study, it can be concluded that at the preliminary and selection stages of the airplane design, the mutual interference between the propeller slipstream and the tail wing can be simplified to be a one-way effect of the slipstream on the tail wing, and the effect of the tail wing on the slipstream can be ignored.
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