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Computational methods for high-Reynolds number viscous flows around complex configurations.

复杂结构周围高雷诺数粘性流的计算方法。

基本信息

批准号：
04650055
负责人：
NAKAHASHI Kazuhiro
金额：
$ 1.28万
依托单位：
TOHOKU UNIVERSITY (1993-1994)Osaka Prefecture University (1992)
依托单位国家：
日本
项目类别：
Grant-in-Aid for General Scientific Research (C)
财政年份：
1992
资助国家：
日本
起止时间：
1992 至 1994
项目状态：
已结题

项目摘要

The computational fluid dynamics (CFD) has undergone an exceptional growth in the last 30 years. Now the state of the art in the area of CFD has evolved to the ability to evaluate the flow about complex, complete aircraft configurations by solving Euler and Reynolds-averaged Navier-Stokes equations. However simulations of the high Reynolds number flow about a three-dimensional body are still far from the practical use for the routine design works. One of the real bottlenecks is the time-consuming procedure to generate an appropriate grid around a complex configuration. The development of the suitable meshing schemes is still an ongoing process, especially for three-dimensional viscous flow simulations.To circumvent this situation, a development of unstructured grid methods has been accelerated from mid 80's because of their attractive capabilities for complex configurations. However, even with these rapid improvements, the unstructured grid methods cannot attain superiority over the structured grid methods yet. This is mainly because of the painful inefficiency of the unstructured grid methods when compared to available structured grid methods.In this research, a new method using a prismatic grid has been developed to compute high-Reynolds number viscous flow fields around complex configurations of aeronautical applications. It includes a prismatic grid generation method and the finite volume flow solvers. The capability of the method was demonstrated by applying it for flow computations around Boeing 747 airplane models.The prismatic grid approach is a practical compromise between structured and unstructured grid approaches for external viscous flow problems. Work is now underway to treat more complex configurations including internal flow problems. For this purpose, a combination of the prismatic grid for the boundary layr regions and the tetrahedral grid for the remaining region is a very promising approach.

计算流体动力学（CFD）在过去的30年里经历了非凡的发展。现在，CFD领域的最新技术已经发展到能够通过求解Euler和reynolds -average Navier-Stokes方程来评估复杂、完整的飞机结构的流动。然而，三维物体高雷诺数流动的模拟在日常设计工作中离实际应用还很遥远。真正的瓶颈之一是围绕复杂配置生成适当网格的过程非常耗时。合适的网格划分方案的发展仍然是一个持续的过程，特别是对于三维粘性流动的模拟。为了避免这种情况，非结构化网格方法的发展从80年代中期开始加速，因为它们具有复杂配置的吸引力。然而，即使有了这些快速的改进，非结构化网格方法仍不能取得优于结构化网格方法的优势。这主要是因为与可用的结构化网格方法相比，非结构化网格方法效率低下。在本研究中，提出了一种利用棱柱网格计算航空应用中复杂结构周围高雷诺数粘性流场的新方法。它包括一个棱柱网格生成方法和有限体积流求解器。通过对波音747飞机模型的流场计算，验证了该方法的有效性。圆柱网格法是一种介于结构化网格法和非结构化网格法之间的实用方法。目前正在进行的工作是处理更复杂的配置，包括内部流动问题。为此，边界层区域的棱柱网格和剩余区域的四面体网格的组合是一种非常有前途的方法。