A range of quasi-steady and unsteady aerodynamic models are used to predict the aerodynamic forces experienced by a flapping wing and a detailed comparison amongst these predictions in provided. The complexity of the models ranges from the analytical potential flow model to the computational Unsteady Vortex Lattice Method (UVLM), which allows one to describe the motion of the wake and account for its influence on the fluid loads. The novelty of this effort lies in a modification of the predicted forces as a generalisation of the leading edge suction analogy. This modification is introduced to account for the delayed stall mechanism due to leading edge flow separation. The model predictions are compared with two sets of independent experimental data and with computational fluid dynamics (CFD) simulation data available in the literature. It is found that both, the modified analytical model and the UVLM model can be used to describe the time history of the lift force, in some cases with better results than a high-fidelity CFD model. The models presented here constitute a useful basis for the aerodynamic design of bioinspired flapping-wings micro-air vehicles.

中文翻译：

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扑翼微型飞行器分析与计算气动模型对比研究

一系列准稳态和非稳态空气动力学模型用于预测扑翼所经历的空气动力，并提供了这些预测之间的详细比较。模型的复杂性范围从分析势流模型到计算非定常涡流点阵法 (UVLM)，它允许人们描述尾流的运动并解释其对流体载荷的影响。这项工作的新颖之处在于将预测力修改为前缘吸力类比的概括。引入这种修改是为了解释由于前沿流动分离导致的延迟失速机制。将模型预测与两组独立的实验数据和文献中可用的计算流体动力学 (CFD) 模拟数据进行比较。发现修改后的解析模型和 UVLM 模型都可以用来描述升力的时间历程，在某些情况下比高保真 CFD 模型的结果更好。这里介绍的模型为仿生扑翼微型飞行器的空气动力学设计提供了有用的基础。