Hyperbolic unstructured grid generation method of three-dimensional complex configuration

ZHANG Qiming; YE Youda; JIANG Qinxue; TIAN Hao

doi:10.7638/kqdlxxb-2021.0186

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Hyperbolic unstructured grid generation method of three-dimensional complex configuration

更新时间：2026-05-28

- Hyperbolic unstructured grid generation method of three-dimensional complex configuration
- Vol. 40, Issue 5, Pages: 175-185(2022)
- 作者机构：
  
  1. 北京流体动力科学研究中心,北京,100120
  2. 国家计算流体力学实验室,北京,100191
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2021.0186
  CLC： V211.3
- Published：2022
- 稿件说明：
移动端阅览
张启明, 叶友达, 蒋勤学, 等. 三维复杂外形的双曲型非结构网格生成方法[J]. 空气动力学学报, 2022, 40(5): 175−186.

ZHANG Qiming, YE Youda, JIANG Qinxue, et al. Hyperbolic unstructured grid generation method of three-dimensional complex configuration[J]. 2022, 40(5): 175-185.
张启明, 叶友达, 蒋勤学, 等. 三维复杂外形的双曲型非结构网格生成方法[J]. 空气动力学学报, 2022, 40(5): 175−186. DOI： 10.7638/kqdlxxb-2021.0186

ZHANG Qiming, YE Youda, JIANG Qinxue, et al. Hyperbolic unstructured grid generation method of three-dimensional complex configuration[J]. 2022, 40(5): 175-185. DOI： 10.7638/kqdlxxb-2021.0186.

摘要

为了实现棱柱网格的自动化生成，发展了使用双曲型偏微分方程生成棱柱网格的方法。利用网格正交性条件和单元体积约束相结合的双曲偏微分方程，从物面网格向外逐步推进生成棱柱形网格。通过类比结构网格双曲型网格生成方法，在非结构网格局部格点坐标系上建立了双曲型网格生成方程，通过格点有限体积法、迎风格式和隐式的方法离散控制方程，使用GMRES求解器求解线性方程组，进而自动生成棱柱网格。该方法应用于球外形、具有尖锐边缘、深凹高凸的旋成体外形、双椭球外形以及X38复杂飞行器，生成的网格表现出良好的正交性和光滑性，表明本文的方法是成功的。数值仿真结果表明本文的网格适用于气动力热的数值模拟。

Abstract

In order to alleviate the workload of the mesh-generation

a method of generating prismatic grids for viscous flow simulations using hyperbolic partial differential equations was developed. Traditional hyperbolic structured grid generation method was restated and the new method was expanded based on this. Combining orthogonality of the grid and the cell volume specification

the prismatic grid front was gradually generated away from the body surface. The hyperbolic grid generation equation described in the local grid point coordinate system was used to discretize the equations through the upwind and implicit methods

and GMRES solver was used to solve the linear equations

so as to generate the new front layer. To address the prismatic mesh collisions in recessed cavities

explicit numerical dissipation was added with the assistant of grid sensor functions. And pseudo-Laplacian was used to smooth the grid. This method was applied to complex shapes with sharp edges

deep concave

strictly convex and X38 configuration. And the generated meshes showed excellent orthogonality and smoothness

which indicates that the method in this paper is successful. The prism grid was utilized in the flow solver in order to improve the accuracy and efficiency of simulation. Numerical simulation results were in good agreement with experiments. The method proposed in this paper is suitable and accurate not only for aerodynamic simulation

but also for aerothermal environment simulation.

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Keywords

references

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