The flapping wing rotor (FWR) is a new type of micro aerial vehicles (MAV), which generates lift through active flapping and passive rotation of antisymmetric wings. Based on the experimental of flapping wings and FWR, the concept of chordwise curved wing is proposed. In this paper, numerical simulations based on Reynolds-averaged Navier Stokes (RANS) equations combined with SST k-ω turbulence model are conducted to study the influence of the height of maximum camber and position of maximum camber on the lift generated by three-wings FWR. Dynamic meshing methods driven by an in-house user-defined function (UDF) are used to model the motion of FWR. The midpoint stroke stage of FWR wings is analyzed in detail. The results show that camber has a great influence on the lift of the FWR. When the maximum camber is less than 0.25c, increase of lift can be achieved for the increase of the maximum camber. And the closer the maximum camber position is to the middle position of the mean aerodynamic chord, the more lift FWR generates.

襟翼旋翼（FWR）是一种新型的微型飞行器（MAV），通过反对称机翼的主动襟翼和被动旋转产生升力。基于襟翼和FWR的实验，提出了弦向弯曲机翼的概念。本文基于雷诺平均Navier Stokes（RANS）方程结合SST k - ω进行数值模拟进行了湍流模型研究最大弯度的高度和最大弯度的位置对三翼FWR产生升力的影响。内部用户定义函数（UDF）驱动的动态网格划分方法用于对FWR的运动进行建模。对FWR机翼的中点行程阶段进行了详细分析。结果表明，外倾对FWR的升力有很大的影响。当最大外倾角小于0.25c时，可以通过增加最大外倾角来实现升力的增加。最大外倾位置越接近平均空气动力弦的中间位置，FWR产生的升力就越大。