适用于非定常流模拟的分布式并行GMRES方法

陈龙; 夏健; 田书玲

doi:10.7638/kqdlxxb-2017.0185

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适用于非定常流模拟的分布式并行GMRES方法

研究论文 | 更新时间：2026-05-28

- 适用于非定常流模拟的分布式并行GMRES方法
- A GMRES method on distributed parallel computers for unsteady flow simulation
- 空气动力学学报 2019年37卷第5期页码：834-843
- 作者机构：
  
  南京航空航天大学非定常空气动力学与流动控制工信部重点实验室,南京,210016
- 作者简介：
  
  陈龙(1983-), 男, 河北赵县人, 博士, 讲师, 研究方向:计算流体力学.E-mail:lchen@nuaa.edu.cn
- 基金信息：
  
  江苏高校优势学科建设工程资助项目（PAPD）
- DOI：10.7638/kqdlxxb-2017.0185
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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陈龙, 夏健, 田书玲. 适用于非定常流模拟的分布式并行GMRES方法[J]. 空气动力学学报, 2019, 37(5): 834-843.

CHEN Long, XIA Jian, TIAN Shuling. A GMRES method on distributed parallel computers for unsteady flow simulation[J]. 2019, 37(5): 834-843.
陈龙, 夏健, 田书玲. 适用于非定常流模拟的分布式并行GMRES方法[J]. 空气动力学学报, 2019, 37(5): 834-843. DOI： 10.7638/kqdlxxb-2017.0185.

CHEN Long, XIA Jian, TIAN Shuling. A GMRES method on distributed parallel computers for unsteady flow simulation[J]. 2019, 37(5): 834-843. DOI： 10.7638/kqdlxxb-2017.0185.

摘要

为提高计算流体力学方法的收敛性和对高性能并行计算机的适应性，发展了适用于非定常流模拟的GMRES并行全隐式方法，并开展了相应的收敛和并行特性研究。采用变子空间数GMRES方法，减小重启过程计算时间；通过分区并行和Hybrid LU-SGS预处理算子实现方法的分布式并行化；采用鲁棒的Negative-SA湍流模型获得更大CFL数，采取计算和存储雅可比矩阵、网格重排序方法提高计算效率。利用这套方法完成了平面流、NACA0012翼型扰流、翼身组合体扰流、F-16战斗机非定常气动弹性和旋翼前飞流场的数值模拟。结果表明其计算效率较LU-SGS方法提高20%~200%；适用于当代高性能计算机分布式并行结构，并行效率非常高，在240个计算核心上出现了加速比的超线性。

Abstract

To improve the computational efficiency and applicability for high performance parallel computing of CFD

a parallel full-implicit method based on GMRES+LU-SGS is developed for unsteady flow simulation. The convergence and parallel property of the method have been studied. The restartable GMRES method is improved to save computing time in the process of GMRES restart. The domain decomposition and Hybrid LU-SGS preconditioner have been studied for parallel implementation. A robust Negative-SA turbulence model for large CFL number

computing and storing the Jacobian matrix and grid reorder methods have been studied to improve the computational efficiency. The methods have been used to compute the plane flow

the flow around NACA0012 airfoil

wing-body configuration

F-16 fighter aeroelastics

and rotor unsteady flow simulation. The numerical results indicate that these methods on distributed parallel computers lead to 20%~200% increase in performance over LU-SGS method. Moreover

remarkable super-linear speedup is achieved on 240 processors.

关键词

Keywords

references

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