A GMRES method on distributed parallel computers for unsteady flow simulation

CHEN Long; XIA Jian; TIAN Shuling

doi:10.7638/kqdlxxb-2017.0185

English Version Journal Login

您当前的位置：

首页 >

文章列表页 >

A GMRES method on distributed parallel computers for unsteady flow simulation

更新时间：2026-05-28

- A GMRES method on distributed parallel computers for unsteady flow simulation
- Vol. 37, Issue 5, Pages: 834-843(2019)
- 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：
- 基金信息：
- DOI：10.7638/kqdlxxb-2017.0185
  CLC： V211.3
- Published：2019
- 稿件说明：
移动端阅览
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

SLOTNICK J, KHODADOUST A, ALONSO J, et al. CFD vision 2030 study: A path to revolutionary computational aero-sciences: NASA-2014-218178[R]. Hampton: NASA, 2014.

ZHANG L P, DENG X G, HE L, et al. The opportunity and grand challenges in computational fluid dynamics by exascale computing[J]. Acta Aerodynamica Sinica, 2016, 34(4):405-417. (in Chinese)

SHAROV D, LUO H, BAUM J. Implementation of unstructured grid GMRES+LU-SGS method on shared-memory, cache-based parallel computers: AIAA-2000-0927[R]. Reno: AIAA, 2000.

KANG Z L, YAN C. Parallel GMRES+LU-SGS method for mixed grids[J]. Acta Aerodynamica Sinica, 2013, 31(2):225-230. (in Chinese)

BROWN D A, ZINGG D W. Performance of a Newton-Krylov-Schur algorithm for solving steady turbulent flows[J]. AIAA Journal, 2016, 54(9):2645-2658.

OSUSKY L, BUCKLEY H, REIST T, et al. Drag minimization based on the Navier-Stokes equations using a Newton-Krylov approach[J]. AIAA Journal, 2015, 53(6):1555-1577.

ITO Y, MURAYAMA M, HASHIMOTO A, et al. TAS Code, FaSTAR and Cflow results for the sixth drag prediction workshop[C]. 55th AIAA Aerospace Sciences Meeting. 2017.

YAN Z G, LIU H Y, MAO M L, et al. Convergence property investigation of GMRES method based on high-order dissipative compact scheme[J]. Acta Aeronoutica et Astronautica Sinica, 2014, 35(2):1181-1192. (in Chinese)

ZHANG J, DENG Y Q, LI B, et al. A new method to accelerate GMRES's convergence applying to three-dimensional hybrid grid[J]. Acta Aeronoutica et Astronautica Sinica, 2016, 37(11):3226-3235. (in Chinese)

GONG X Q, JIA H Y, CHEN J T, et al. Applications of GMRES based on exact calculations of Jacobian matrix in discontinuous Galerkin methods[J]. Acta Aerodynamica Sinica, 2019, 37(1):121-132. (in Chinese)

XIA J, TIAN S L, WANG J F, et al. Parallel computing strategy for 3d dynamic overset unstructured Navier-Stokes solver[J]. Acta Aeronoutica et Astronautica Sinica, 2008, 29(5):1118-1124. (in Chinese)

ALLMARAS S R, JOHNSON F T, SPALART P R. Modifications and clarifications for the implementation of the Spalart-Allmaras turbulence model: ICCFD7-1902[C]//Big Island: ICCFD, 2012.

Saad Y. GMRES:Iterative methods for sparse linear systems[M]. 2nd ed. Philadelphia:SIAM, 2003.

CHEN J, WANG Z H. Scalability analysis of CFD parallel applications[J]. Acta Aerodynamica Sinica, 2002, 20(3):22-26. (in Chinese)

WISSINK A M. Parallelization of a three-dimensional flow solver for Euler rotorcraft aerodynamics predictions[J]. AIAA Journal, 1996, 34(11):2276-2282.

GIBBS N E, POOLE W G, STOCKMEYER P K. An algorithm for reducing the bandwidth and profile of a sparse matrix[J]. SIAM J Numer Anal, 1976, 13:236-250.

DAVID H, FORSYTHE J, HALLISSY B P, el al. Fundamental physics validation using CREATE-AV kestrel part I: AIAA 2014-0920[R]. Maryland: AIAA, 2014.

MURAYAMA M, YAMAMOTO K. Comparison study of drag prediction by structured and unstructured mesh method[J]. Journal of Aircraft, 2008, 45(3):799-822.

RUMSEY C L, RIVERS S M, MORRISON J H. Study of CFD variation on transport configurations from the second drag-prediction workshop[J]. Computers Fluids, 2004, 34(7):785-816.

ABDOL-HAMID K S, CARLSON J, RUMSEY C L, el al. DPW-VI results using FUN3D with focus on k-kL-MEAH 2015 turbulence mode: NF1676L-25300l[R]. Hampton: NASA, 2017.

PARKER G. Dynamic aeroelastic analysis of wing/store configurations: AD-445218[R]. Ohio: AFIT, 2005.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Gust loads alleviation of flying wing aircraft based on jet flow control

A parallel fast iteration method for wall distance implemented in PHengLEI

Aerodynamic and wind energy harvesting integrative design for UAVs

Engine cooling fan layout study of a medium size pickup truck

Development and application of a credibility assessment platform for CFD software

Related Author

Xia Yuhang

Guo Pengyu

Liao Xueqi

Zhang Weiyuan

Shi Zhiwei

Mei Yang

Zhou Hanyu

Wang Siyuan

Related Institution

College of Aerospace Engineering, Nanjing University of Aeronautics And Astronautics, Nanjing

School of Aerospace Engineering, Tsinghua University, Beijing

School of Aeronautics, Northwestern Polytechnical University, Xi'an

National Key Laboratory of Aircraft Configuration Design, Xi'an

Vehicle Technology section, Model Development Department, Technology Center, Zhengzhou Nissan Automobile CO. , LTD, Zhengzhou

AI问答

⁰