<p>The compound tilt-wing aircraft is a new type of vertical take-off and landing aircraft that combines the advantages of tilt-wing and compound configurations, such as high efficiency, high speed, and high stability. However, during the tilt transition phase, the aircraft’s aerodynamic characteristics show nonlinearity, strong coupling, and unsteadiness. This paper formulates a numerical computation method that utilizes the sliding mesh technique and momentum source method to effectively simulate the tilt transition phase of compound tilt-wing aircraft. It examines and analyzes the impact of various factors like the position of the lift rotors, freestream velocities, tilt velocity, and the aerodynamic characteristics during take-off and return phases of the wing. The results indicate that the radial position of the lift rotors has minimal effect on the wing’s aerodynamic interference characteristics, while the axial position has a significant influence. The optimal aerodynamic effect is achieved when the lift rotors are placed 0.35&#xa0;m below the lower surface of the wing. The steady-state and unsteady-state calculations yield similar trends in the variation of aerodynamic forces on a wing as the tilt angle increases, but they differ in the phase and magnitude of the extreme values, which are also significantly influenced by the freestream velocity. The take-off and return transition phases present distinct aerodynamic characteristics, and variations in tilt velocity also have a certain impact on their aerodynamic properties.</p>