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三维可压和不可压缩流动数值模拟的一种预处理多重网格方法研究(英文)
引用本文:韩忠华,何飞,宋文萍,乔志德.三维可压和不可压缩流动数值模拟的一种预处理多重网格方法研究(英文)[J].中国航空学报,2007,20(4):289-296.
作者姓名:韩忠华  何飞  宋文萍  乔志德
作者单位:西北工业大学翼型、叶栅国防科技重点实验室,西北工业大学翼型、叶栅国防科技重点实验室,西北工业大学翼型、叶栅国防科技重点实验室,西北工业大学翼型、叶栅国防科技重点实验室
基金项目:Science and Technical Foundation of National Key Laboratory of Aerodynamic Design and Research (9140C4202020604)
摘    要:将矩阵预处理方法与多重网格方法结合,发展了适用于机翼及复杂外形气动数值优化设计的高效数值模拟方法和程序。在不改变定常流动解的前提下,对 Navier-Stokes 方程的时间导数项实施 Choi-Merkle 矩阵预处理,从而改善可压缩控制方程在低速情况下的系统刚性。Choi-Merkle 预处理最初用于二维低马赫数粘性流动数值模拟,本文将其推广应用到计算三维流动,并针对提高跨音速流动计算收敛性进行了相应的改进。预处理后控制方程采用中心格式有限体积进行空间离散,Runge-Kutta 混合多步方法进行显式时间推进求解,并应用 FAS 多重网格方法加速收敛。采用所发展的方法和程序数值模拟了绕 M6 机翼和 M100 机翼的低速和跨音速流动(马赫数从0.01 到 0.839)以及绕 F4 翼身组合体流动。计算结果与实验值吻合良好,验证了所发展的方法的正确性。算例研究表明所发展方法较大幅度地提高了三维流动数值模拟的效率,且同时适用于可压和不可压流动计算,在机翼及复杂外形气动优化设计方法具有应用前景

关 键 词:Navier-Stokes方程  预处理方法  多重网格方法  数值模拟

A Preconditioned Multigrid Method for Efficient Simulation of Three-dimensional Compressible and Incompressible Flows
Han Zhonghua,He Fei,Song Wenping,Qiao Zhide.A Preconditioned Multigrid Method for Efficient Simulation of Three-dimensional Compressible and Incompressible Flows[J].Chinese Journal of Aeronautics,2007,20(4):289-296.
Authors:Han Zhonghua  He Fei  Song Wenping  Qiao Zhide
Abstract:To develop an efficient and robust aerodynamic analysis method for numerical optimization designs of wing and complex configuration, a combination of matrix preconditioning and multigrid method is presented and investigated. The time derivatives of three-dimensional Navier-Stokes equations are preconditioned by Choi-Merkle preconditioning matrix that is originally designed for two-dimensional low Mach number viscous flows. An extension to three-dimensional viscous flow is implemented, and a method improving the convergence for transonic flow is proposed. The space discretizaition is performed by employing a finite-volume cell-centered scheme and using a central difference. The time marching is based on an explicit Runge-Kutta scheme proposed by Jameson. An effficient FAS multigrid method is used to accelerate the convergence to steady-state solutions. Viscous flows over ONERA M6 wing and M100 wing are numerically simulated with Mach numbers ranging from 0.010 to 0.839. The inviscid flow over the DLR-F4 wing-body configuration is also calculated to preliminarily examine the performance of the presented method for complex configuration. The computed results are compared with the experimental data and good agreement is achieved. It is shown that the presented method is efficient and robust for both compressible and incompressible flows and is very attractive for aerodynamic optimization designs of wing and complex configuration.
Keywords:Navier-Stokes equations  preconditioning method  multigrid method  numerical simulation  Incompressible Flows  Simulation  Efficient  incompressible flows  aerodynamic optimization  computed  results  experimental data  good  inviscid flow  performance  Viscous  simulated  Mach  numbers  ranging  used  accelerate  solutions  marching
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