基于动量叶素理论建立了涵盖悬停、倾斜前飞和高速巡航多飞行状态倾转旋翼气动性能计算模型，将计算模型配合NSGA-II多目标遗传算法，以倾转旋翼悬停、倾斜前飞和高速巡航飞行效率为优化目标，桨叶翼型展向分布、弦长和扭转角等参数为优化变量，设计了一款倾转旋翼。采用由经典的分离涡模拟方法（DES）改进得到的延迟分离涡模拟方法（DDES）对旋翼流场进行模拟仿真，捕获了较高精度的流场尾迹，分析了倾转旋翼流场的诱导速度分布，同时验证了动量叶素理论计算模型具有较高准确性和可信度。计算结果表明，同样飞行工况下，相较于原倾转旋翼模型，悬停效率从71.78%提高到75.34%，巡航效率从62.93%提高到71.32%。

A calculation model for the aerodynamic performance of tiltrotors was established based on the blade element momentum theory, covering multiple flight conditions of hover, tilt forward flight, and high-speed cruise. The calcu-lation model was combined with the NSGA-II multi-objective genetic algorithm to optimize the efficiency of the tiltrotor in hover, tilt forward flight, and high-speed cruise flight conditions. Parameters such as blade airfoil selec-tion distribution, chord length, and twist angle were used as optimization variables to design a tiltrotor. The rotor flow field was simulated by using the delayed detached eddy simulation (DDES) method improved from the classical detached eddy simulation (DES). The flow wake with high accuracy was captured, and the induced velocity distribu-tion of the tiltrotor flow field was analyzed. At the same time, the high accuracy and reliability of the blade element momentum theory theoretical calculation model were verified. The calculation results show that under the same flight conditions, compared to the original tiltrotor model, the hovering efficiency increases from 71.78% to 75.34%, and the cruising efficiency increases from 62.93% to 71.32%.