螺旋桨梢涡流场的DES模拟

摘要

文章应用分离涡模型（DES）对螺旋桨尾流中梢涡流场分布进行了数值研究。为准确模拟螺旋桨梢涡流场的信息，应用全六面体网格对螺旋桨计算域进行网格划分，通过迭代计算确定螺旋桨梢涡涡核的位置。为避免数值离散误差，对梢涡区域进行了网格加密处理。为了研究螺旋桨梢涡空间形态，文中采用涡核识别的“Q准则”，对螺旋桨梢涡等值面进行定义。计算结果表明，该文建立的尾流中梢涡流场分布数值模拟方法能够准确预报出螺旋桨梢涡流场的分布及涡核形状，与实验测量结果相符。%Based on the Detached Eddy Simulation model, the tip vortex flow field of the propeller in the wake is investigated. A structure grid is generated for the current computational domain. To re-duce the discrete error caused by the grid, the mesh refinement is applied to the area of tip vortex core in the numerical simulation. In order to do research on the tip vortex, ‘Q-Criterion’ is used to define the structure of vortex. The calculated results show that the numerical method can exactly pre-dict the velocity distribution, vortex core location and vortex structures in tip vortex formation and evolution.