论文标题
飞机机翼上的基于卷的胶卷流量和冰振动模型
Finite volume based film flow and ice accretion models on aircraft wings
论文作者
论文摘要
本文研究了由气体流动，压力梯度和重力驱动的稀薄回滚水膜。提出了基于有限体积方法（FVM）和润滑理论的三维膜流模型来描述流动。膜的深度平均速度存储在笛卡尔坐标中，以避免公制张量的出现。控制方程在第一层结构性网格单元中被离散化，该电网被选为膜流的网格。为了验证这种方法，提出了NACA 0012机翼和GLC-305 SCHEPT机翼的数值结果与实验结果之间的比较，两者都显示出与RIME和釉面冰条件的良好一致性。总体而言，该模型显示出在不同的结冰条件下合理地对冰增生建模的巨大潜力。此外，目前的方法不需要分析度量术语，并且可以轻松地与现有的有限体积求解器耦合到逻辑上的笛卡尔网格。
The thin runback water films driven by the gas flow, the pressure gradient and the gravity on the iced aircraft surface are investigated in this paper. A three-dimensional film flow model based on Finite Volume Method (FVM) and the lubrication theory is proposed to describe the flow. The depth-averaged velocity of the film is stored in Cartesian coordinates to avoid the appearance of the metric tensors. The governing equations are discretized in the first layer structured grid cell which is selected as the grids for film flow. In order to verify this method, comparisons between numerical results and experimental results of ice shapes on NACA 0012 airfoil and GLC-305 swept wing are presented, both showing a good agreement for rime and glaze ice condition. Overall, this model shows great potential to model ice accretion reasonably under different icing conditions. Besides, the present method doesn't require analytic metric terms, and can be easily coupled to existing finite volume solvers for logically Cartesian meshes.
