中文摘要：

针对微型扑翼所处典型飞行状态,数值模拟研究了微型扑翼绕流的低雷诺数气动特性。基于结构化嵌套网格求解了预处理后的三维非定常雷诺平均Navier-Stokes方程,空间离散采用了中心格式有限体积法,非定常时间推进为双时间法。通过与文献低雷诺数扑翼的试验值对比验证了本文算法的有效性,接下来通过大量计算研究了关键气动参数和展向折叠扑动模式的影响规律。研究结果表明迎角、扭转角和折叠扑动对升力影响较大,扭转角和减缩频率对推力影响较大。本文的研究得到了微型扑翼气动力特性的机理性结论,有助于理解微型扑翼飞行原理,为设计微型扑翼提供了参考依据。

英文摘要：

The aerodynamic performance of micro flapping-wing in low Reynolds number flow is researched by numerical simulation.The numerical method is solving preconditioned Reynolds-averaged Navier-Stokes equations based on structured chimera grid method.The spatial discretization is cell centered finite volume method.The dual time method is used in unsteady iteration.The validity of code is verified by good accordance between experiment results of reference and calculated results of this paper.The key parameters,including angle of attack,pitching angle,plunging angle,and reduced frequency are researched.Then the folding flapping mode is researched.The results show that the angle of attack,pitching angle and flapping mode affect the lift very much,but the pitching angle and reduced frequency affect the thrust a lot.Special designed flapping motion can improve the aerodynamic performance of flapping wing.The research of this paper is helpful to understand the mechanism of flapping flight and useful to design flapping wing micro air vehicles.