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Pseudopotential-based discrete unified gas kinetic scheme for modeling multiphase fluid flows

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Advances in Aerodynamics 2022年第1期4卷 662-687页

作者： Zeren Yang Sha Liu congshan zhuo Chengwen Zhong School of Aeronautics Northwestern Polytechnical University127 West Youyi Road710072Xi’anChina National Key Laboratory of Science and Technology on Aerodynamic Design and Research Northwestern Polytechnical University127 West Youyi Road710072Xi’anChina

To directly incorporate the intermolecular interaction effects into the discrete unified gas-kinetic scheme(DUGKS)for simulations of multiphase fluid flow,we developed a pseudopotential-based DUGKS by coupling the pseudopotential model that mimics the intermolecular interaction into *** to the flux reconstruction procedure,additional terms that break the isotropic requirements of the pseudopotential model will be *** eliminate the influences of nonisotropic terms,the expression of equilibrium distribution functions is reformulated in a moment-based *** the isotropy-preserving parameter appropriately tuned,the nonisotropic effects can be properly canceled *** fundamental capabilities are validated by the flat interface test and the quiescent droplet *** has been proved that the proposed pseudopotential-based DUGKS managed to produce and maintain isotropic *** isotropy-preserving property of pseudopotential-based DUGKS in transient conditions is further confirmed by the spinodal *** superiority of the pseudopotential-based DUGKS over the lattice Boltzmann method is also demonstrated by predicting the coexistence densities complying with the van der Waals equation of *** directly incorporating the intermolecular interactions,the pseudopotential-based DUGKS offers a mesoscopic perspective of understanding multiphase behaviors,which could help gain fresh insights into multiphase fluid flow.

关键词： Pseudopotential model Discrete unified gas kinetic scheme Multiphase flows Isotropic interface

Large-eddy simulation of wall-bounded turbulent flow with high-order discrete unified gas-kinetic scheme

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Advances in Aerodynamics 2020年第1期2卷 528-554页

作者： Rui Zhang Chengwen Zhong Sha Liu congshan zhuo School of Aeronautics Northwestern Polytechnical University127 West Youyi Road710072Xi’anPeople’s Republic of China National Key Laboratory of Science and Technology on Aerodynamic Design and Research Northwestern Polytechnical University127 West Youyi Road710072Xi’anPeople’s Republic of China

In this paper,we introduce the discrete Maxwellian equilibrium distribution function for incompressible flow and force term into the two-stage third-order Discrete Unified Gas-Kinetic Scheme(DUGKS)for simulating low-speed turbulent *** Wall-Adapting Local Eddy-viscosity(WALE)and Vreman sub-grid models for Large-Eddy Simulations(LES)of turbulent flows are coupled within the present ***,the implicit LES are also presented to verify the effect of LES models.A parallel implementation strategy for the present framework is developed,and three canonical wall-bounded turbulent flow cases are investigated,including the fully developed turbulent channel flow at a friction Reynolds number(Re)about 180,the turbulent plane Couette flow at a friction Re number about 93 and lid-driven cubical cavity flow at a Re number of *** turbulence statistics,including mean velocity,the *** velocity,Reynolds stress,*** computed by the present *** predictions match precisely with each other,and they are both in reasonable agreement with the benchmark data of ***,the predicted flow physics of three-dimensional lid-driven cavity flow are consistent with the description from abundant *** present numerical results verify that the present two-stage third-order DUGKS-based LES method is capable for simulating inhomogeneous wall-bounded turbulent flows and getting reliable results with relatively coarse grids.

关键词： Large-eddy simulation Wall-bounded turbulent flow DUGKS High order scheme

Application of Lattice Boltzmann Method to Simulation of Compressible Turbulent Flow

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Communications in Computational Physics 2010年第10期8卷 1208-1223页

作者： congshan zhuo Chengwen Zhong Kai Li Shengwei Xiong Xiaopeng Chen Jun Cao National Key Laboratory of Science and Technology on Aerodynamic Design and Research Northwestern Polytechnical UniversityXi’anShaanxi 710072China Center for High Performance Computing Northwestern Polytechnical UniversityXi’anShaanxi 710072China School of Mechanics Civil Engineering and ArchitectureNorthwestern Polytechnical UniversityXi’anShaanxi 710072China Department of Mechanical and Industrial Engineering Ryerson UniversityTorontoOntarioM5B 2K3Canada

The main goal of this paper is to develop the coupled double-distributionfunction(DDF)lattice Boltzmann method(LBM)for simulation of subsonic and transonic turbulent *** the present study,we adopt the second-order implicit-explicit(IMEX)Runge-Kutta schemes for time discretization and the Non-Oscillatory and NonFree-Parameters Dissipative(NND)finite difference scheme for space *** Sutherland’s law is used for expressing the viscosity of the fluid due to considerable temperature ***,the Spalart-Allmaras(SA)turbulence model is incorporated in order for the turbulent flow effect to be *** experiments are performed on different turbulent compressible flows around a NACA0012 airfoil with body-fitted *** numerical results are found to be in good agreement with experiment data and/or other numerical solutions,demonstrating the applicability of the method presented in this study to simulations of both subsonic and transonic turbulent flows.

关键词： Lattice Boltzmann method compressible turbulent flow airfoil body-fitted grid

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高雷诺数下的翼型绕流LBM数值模拟

航空学报 2010年第2期31卷 238-243页

作者：卓丛山钟诚文李凯解建飞张勇西北工业大学翼型、叶栅空气动力学国防科技重点实验室陕西西安710072 西北工业大学高性能计算研究与发展中心陕西西安710072 中国人民解放军96125部队广西柳州545000

采用格子Boltzmann方法(LBM)的二维9速度(D2Q9)模型和贴体网格,通过引入非均匀网格插值方法和非平衡态外推边界处理,分别结合Baldwin-Lomax(B-L)湍流模型和Spalart-Allmaras(S-A)湍流模型,对高雷诺数Re≥5×105下的NACA0012翼型绕流进... 详细信息

采用格子Boltzmann方法(LBM)的二维9速度(D2Q9)模型和贴体网格,通过引入非均匀网格插值方法和非平衡态外推边界处理,分别结合Baldwin-Lomax(B-L)湍流模型和Spalart-Allmaras(S-A)湍流模型,对高雷诺数Re≥5×105下的NACA0012翼型绕流进行了数值模拟和对比研究,两者的结果与CFL3D的结果和实验结果均吻合的很好,相比之下,采用S-A模型能更好地预测失速迎角,其处理分离流动的能力要强于B-L模型。改进后的LBM适用于非均匀贴体网格,曲边边界,计算简单,并可应用于更复杂的高雷诺数流动中。

关键词：格子Boltzmann方法高雷诺数流动非均匀贴体网格翼型

一种求解低速跨流域流固耦合问题的离散统一气体动理学格式

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空气动力学学报 2022年第3期40卷 87-97,I0002页

作者：王勇刘沙卓丛山钟诚文西北工业大学航空学院西安710072 西北工业大学翼型、叶栅空气动力学重点实验室西安710072

运动边界及流固耦合问题是低速及高速、连续流域及稀薄流域流动中常面临的多场耦合问题。本文在原始离散统一气体动理学格式基础上,采用任意拉格朗日-欧拉方法及动网格技术,并耦合计算结构动力学,实现适用于低速流动运动边界及流固耦合... 详细信息

运动边界及流固耦合问题是低速及高速、连续流域及稀薄流域流动中常面临的多场耦合问题。本文在原始离散统一气体动理学格式基础上,采用任意拉格朗日-欧拉方法及动网格技术,并耦合计算结构动力学,实现适用于低速流动运动边界及流固耦合问题的计算方法。在方法验证方面,进行连续流域圆柱绕流强迫振动和自由振动数值模拟,计算结果与参考文献结果吻合良好,准确捕捉圆柱在锁频区和非锁频区的流动特性。在稀薄流域范围,将方法中的连续流D2Q9离散速度模型替换成跨流域离散速度模型,对比低速圆柱绕流强迫振动算例在两种离散速度模型下的数值结果。虽主要关注低速流动问题,但发展的算法仍具备模拟高超声速运动边界问题的能力,对此进行了Ma=5.0稀薄流振动圆柱研究。低速和高速运动边界模拟能力显示了方法在考虑稀薄气体效应流固耦合问题方面的潜在应用价值。

关键词：离散统一气体动理学格式任意拉格朗日-欧拉方法流固耦合圆柱绕流稀薄气体效应

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双原子分子气体的定常隐式全流域多尺度算法

国防科技大学学报 2023年第4期45卷 94-108页

作者：钟诚文陈健锋张瑞卓丛山刘沙西北工业大学航空学院陕西西安710072 西北工业大学极端力学研究院陕西西安710072 西北工业大学翼型、叶栅空气动力学国家级重点实验室陕西西安710072

巨大的计算资源需求极大地阻碍了统一气体动理学格式的应用。采用宏观预估技术,基于Boltzmann-Rykov模型方程发展全流域适用的保守恒定常隐式算法,协同求解宏观方程和微观方程以加速收敛。在单元界面,通过模型方程特征差分解构造简单高... 详细信息

巨大的计算资源需求极大地阻碍了统一气体动理学格式的应用。采用宏观预估技术,基于Boltzmann-Rykov模型方程发展全流域适用的保守恒定常隐式算法,协同求解宏观方程和微观方程以加速收敛。在单元界面,通过模型方程特征差分解构造简单高效的多尺度数值通量,并结合非均匀非结构速度空间和速度空间自适应技术进一步降低计算需求、提升计算效率。超声速和高超声速平板绕流和圆球绕流的数值结果验证了算法的准确性与高效性。结果表明,算法能够准确求解二维和三维双原子气体多尺度流动问题,且相比于显式离散统一气体动理学格式可加速一个量级。

关键词：多尺度算法隐式算法稀薄气体双原子气体

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气体运动论BGK格式的翼型绕流数值模拟

航空学报 2010年第6期31卷 1099-1105页

作者：熊生伟钟诚文卓丛山李凯陈效鹏西北工业大学翼型叶栅空气动力学国家重点实验室陕西西安710072 西北工业大学高性能计算研究与发展中心陕西西安710072 西北工业大学力学与土木建筑学院陕西西安710072

以气体运动论BGK(Bhatnagaar-Gross-Krook)格式为基础,通过改进非均匀网格下的通量计算方法,把气体运动论BGK方法应用到二维贴体网格上模拟了可压缩的无黏和黏性流动。在重构阶段,以交界面周围4个网格单元为一组,先把每个网格单元的宏观... 详细信息

以气体运动论BGK(Bhatnagaar-Gross-Krook)格式为基础,通过改进非均匀网格下的通量计算方法,把气体运动论BGK方法应用到二维贴体网格上模拟了可压缩的无黏和黏性流动。在重构阶段,以交界面周围4个网格单元为一组,先把每个网格单元的宏观量(密度、动量和总能量)转换在相对于交界面的坐标系下,然后使用van Leer限制器插值求出交界面的宏观量,在求解阶段再使用BGK理论求出流过交界面的通量。通过上述方法使贴体网格和均匀网格,在计算格式上一致,与其他求解二维贴体网格的气体运动论BGK方法相比,该方法相对简单,计算量减小。结合贴体网格通量计算和气体运动论BGK格式方法理论,分别对亚、跨、超声速下的NACA0012翼型绕流进行了数值模拟和对比研究,所得可压缩无黏流动的数值结果与北大西洋公约组织航天研究与发展咨询组(AGARD)的结果吻合良好。本文还模拟了低雷诺数状态下的可压缩黏性流动,所得结果与文献中的数值计算结果吻合良好,证明了该方法在数值模拟及激波捕捉方面具有鲁棒性,为在复杂流动中的应用提供了一种简单的途径。

关键词： BGK 气体运动论非均匀贴体网格翼型

多图形处理器上Lattice-Boltzmann方法的加速

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计算机辅助设计与图形学学报 2010年第11期22卷 1932-1939页

作者：吴亮钟诚文郑彦奎刘沙卓丛山陈效鹏西北工业大学高性能计算研究与发展中心西安710072 西北工业大学翼型、叶栅空气动力学国防科技重点实验室西安710072 西北工业大学力学与土木建筑学院西安710072

为了提高计算流体领域中复杂流动现象模拟计算的高效性和准确性,充分利用图形硬件的并行性,提出一种在单机多图形处理器下基于CUDA架构的Lattice Boltzmann方法(LBM)的模拟算法.采用区域划分策略将域上的LBM网格平均分配到不同的GPU设备... 详细信息

为了提高计算流体领域中复杂流动现象模拟计算的高效性和准确性,充分利用图形硬件的并行性,提出一种在单机多图形处理器下基于CUDA架构的Lattice Boltzmann方法(LBM)的模拟算法.采用区域划分策略将域上的LBM网格平均分配到不同的GPU设备上,在分区边界处搭接一层网格以方便计算该处网格的迁移过程,减少GPU间的通信量,并合理地利用CUDA存储层次架构中的全局内存和纹理内存为计算网格分配设备空间;采用多线程技术,用每个线程控制不同的GPU设备,同时引入线程同步机制信号量实现线程间的数据通信同步控制,按照LBM方程组的求解过程实现模拟计算.实验结果表明,双GPU将计算加速到单GPU的1.77倍左右,同时将流场计算网格规模从单GPU下的4160×4160扩大到双GPU下的6144×6144.

关键词： CUDA 多线程技术 Lattice Boltzmann方法多图形处理器信号量并行计算

COMPRESSIBLE FLOW SIMULATION AROUND AIRFOIL BASED ON LATTICE BOLTZMANN METHOD

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Transactions of Nanjing University of Aeronautics and Astronautics 2009年第3期26卷 206-211页

作者：钟诚文李凯孙建红卓从山解建飞西北工业大学航空学院南京航空航天大学航空宇航学院

The flow around airfoil NACA0012 enwrapped by the body-fitted grid is simulated by a coupled doubledistribution-function （DDF） lattice Boltzmann method （LBM） for the compressible Navier-Stokes equations. Firstly, the method is tested by simulating the low Reynolds number flow at Ma =0. 5,a=0. 0, Re=5 000. Then the simulation of flow around the airfoil is carried out at Ma：0. 5, 0. 85, 1.2; a=-0.05, 1.0, 0.0, respectively. And a better result is obtained by using a local refined grid. It reduces the error produced by the grid at Ma=0. 85. Though the inviscid boundary condition is used to avoid the problem of flow transition to turbulence at high Reynolds numbers, the pressure distribution obtained by the simulation agrees well with that of the experimental results. Thus, it proves the reliability of the method and shows its potential for the compressible flow simulation. The suecessful application to the flow around airfoil lays a foundation of the numerical simulation of turbulence.

关键词： compressible flow computational fluid dynamics lattice Boltzmann method airfoil body-fitted grid