For the purpose of improving the accuracy of tilt-rotor aircraft model, a split modeling scheme is proposed instead of the overall modeling: the enhanced Pitt-Peters dynamic inflow model was used to describe the wake distortion effect, and the rotor-induced velocity distribution was modeled based on classical vortex theory and experimental data. Rotor download is taken into account in airfoil modeling, which is modeled by interference coefficient fitting method. The comparison experiments on publicly available data and modeling result prove the correctness of proposed model, and the proposed model can be used for the research of flight mechanics and control simulation of tilt-rotor aircraft with high accuracy.