黏性不可压流体的自适应网格技术和基本特性方程分离算法的联合分析

组合基本特性方程分离算法和自适应网格技术,分析二维黏性不可压流体.该方法使用3节点三角单元,对速度分量和压力等变量分析,使用等阶次的插值函数.组合解法的主要优点在于,在自适应网格技术中,对解梯度变化大的区域,通过耦合误差估计生成小的单元,利于提高解的精度,在其它区域生成大单元,可以节省时间.最后,通过对一个黏性流体圆柱体绕流问题的瞬态和稳态特性分析,给出了组合解法性能的评价.     

多项式基函数法

提出一种新型的数值计算方法--基函数法.此方法直接在非结构网格上离散微分算子,采用基函数展开逼近真实函数,构造出了导数的中心格式和迎风格式,取二阶多项式为基函数,并采用通量分裂法及中心格式和迎风格式相结合的技术以消除激波附近的非物理波动,构造出数值求解无粘可压缩流动二阶多项式的基函数格式,通过多个二维无粘超音速和跨音速可压缩流动典型算例的数值计算表明,该方法是一种高精度的、对激波具有高分辨率的无波动新型数值计算方法,与网格自适应技术相结合可得到十分满意的结果.     

迎风紧致格式与驱动方腔流动问题的直接数值模拟

本文给出了一种求解不可压缩流动问题的高精度差分格式,即迎风紧致格式.出发方程采用二维非定常原始变量Naiver-Stokes方程组.在差分方程中,对流项采用三阶精度的迎风紧致差分,其余空间导数项采用四阶紧致差分.本文利用该差分格式在等距网格上数值模拟了驱动方腔流动中的分离涡运动.在257×257的细网格上,Re数最高计算到10000.Re≤5000时的计算结果与前人结果符合得很好.当Re≥7500时发现流动不存在定常层流解而为非定常周期性解,并首次给出了非定常解的结果。     

一类非线性边值问题解的激波性态

利用激波理论和匹配原理, 在适当的条件下讨论了一类非线性方程的激波问题, 得出了其激波解及其激波位置的表示式.将其结果用于一类可压缩流体流动模型, 较简捷地得到了该模型解的激波性态.     

群速度直接控制四阶迎风紧致格式

为求解多尺度复杂流动在有限网格点的情况下高精度方法是可供选择的方法之一,其中紧致型格式数值解的分辨率更好.用迎风型紧致格式计算激波时,数值解中仍有数值振荡产生,这是由于对应于不同波数之群速度不均一所致.采用群速度直接控制方法重构紧致型格式以提高捕捉激波的能力.该方法简单,精度高,网格基架点少.算例表明,这一新的方法是可行的.     

大变形网格上时间二阶精度扩散方程的保正格式

本文基于已有的连续扩散通量的两点非线性离散格式,构造了2D非稳态扩散方程大变形网格上的两层非线性有限体积格式.该格式利用Crank-Nicolson (C-N)方法的思想在时间方向获得了二阶精度.由于所得代数方程组的系数矩阵的转置是M矩阵,从而能够保持解的正性,并利用Brouwer不动点定理证明了格式解的存在性.数值实验结果表明,在较大时间步长下,该格式具有二阶计算精度.     

激波捕捉差分方法研究

在迎风型格式和矢通量分裂技术的基础之上,对捕捉激波方法进行一种新的尝试．该方法首先对原始格式在特征方向上进行投影,然后用限制器对这些特征分量的变化幅值进行限制以抑止非物理波动,最后再把它转换成守恒形式,得到了基本上无振荡的激波捕捉格式．用该方法对两种迎风显示格式(二阶和三阶)和3种迎风紧致格式(三阶、五阶和七阶)进行处理,并在一维和二维的情况下进行了应用测试．通过与高阶WENO、MP、Compact-WENO等格式的比较,表明该方法在光滑捕捉激波的前提下仍有较高精度和分辨率．     

不可压缩黏性流体的二维Navier-Stokes方程的间断有限元模拟

由于不可压缩Navier-Stokes方程由守恒律、扩散及约束发展方程混合构成,为测试数值方法,该文基于非结构网格,对该方程建立了DG(discontinuous Galerkin)格式,讨论了不同黏性系数ν在方腔涡流问题的数值结果,验证了该方法的有效性且不依赖于问题的维数.圆柱绕流问题的模拟结果进一步表明此方法精度高、可有效求解具有运动界面的不可压缩黏性流体问题,使得模拟边界层、剪切层及复杂涡流解十分有效,并可以成功地推广到解决复杂现象数值模拟中的激波结构.     

奇异摄动反应扩散方程的后验误差估计及自适应算法

研究了一类奇异摄动半线性反应扩散方程的自适应网格方法.在任意非均匀网格上建立迎风有限差分离散格式,并推导出离散格式的后验误差界,然后用该误差界设计自适应网格移动算法.数值实验结果证明了所提出的自适应网格方法的有效性.     

基于网格变动的油水驱动半正定问题迎风混合元方法

在网格随时间变动的有限元空间上研究了不可压缩的两相渗流驱动问题.分别对饱和度方程扩散矩阵正定和半正定的情形,提出了基于网格变动的迎风混合元方法混合元逼进压力方程,饱和度方程的对流项采用迎风格式来处理,扩散项则采用推广的混合元来逼进.在网格任意变动的情形下得到几乎最优的误差估计;对正定问题的格式进行改进,即在两个网格之间投影变化时采取近似解的线性构造,可以得到与固定网格时相同的最优收敛阶.     

Lattice Boltzmann simulation for high-speed compressible viscous flows with a boundary layer

In this study, the lattice Boltzmann method is employed for simulating high-speed compressible viscous flows with a boundary layer. The coupled double-distribution-function lattice Boltzmann method proposed by Li et al. (2007) is employed because of its good numerical stability and non-free-parameter feature. The non-uniform mesh construction near the wall boundary in fine grids is combined with an appropriate wall boundary treatment for the finite difference method in order to obtain accurate spatial resolution in the boundary layer problem. Three typical problems in high-speed viscous flows are solved in the lattice Boltzmann simulation, i.e., the compressible boundary layer problem, shock wave problem, and shock boundary layer interaction problem. In addition, in-depth comparisons are made with the non-oscillatory and non-free-parameter dissipation (NND) scheme and second order upwind scheme in the present lattice Boltzmann model. Our simulation results indicate the great potential of the lattice Boltzmann method for simulating high-speed compressible viscous flows with a boundary layer. Further research is needed (e.g., better numerical models and appropriate finite difference schemes) because the lattice Boltzmann method is still immature for high-speed compressible viscous flow applications.     

一种健壮的低耗散通量分裂格式

随着计算流体力学的快速发展,设计精确、高效并且健壮的数值格式变得尤为重要.通过对3种流行的通量分裂方法(AUSM、Zha-Bilgen和Toro-Vázquez)的对流通量和压力通量进行特征分析,构造了一种简单、低耗散并且健壮的通量分裂格式(命名为R-ZB格式).采用Zha-Bilgen分裂方法将Euler方程的通量分裂成对流通量和压力通量,其中对流通量采用迎风方法来计算,压力通量采用低耗散的HLL格式来计算,从而克服了原始的HLL格式不能精确分辨接触间断的缺点.数值实验表明,该文给出的R-ZB格式不仅保留了原始Zha-Bilgen格式简单高效、能够精确分辨接触间断等优点,而且具有更好的健壮性,在计算二维问题时不会出现数值激波不稳定现象.     

一维活塞问题激波解的整体存在性

本文用改进的Glimm格式的方法,研究一维活塞问题当活塞的运动速度是一个常数的扰动时含有激波的弱解的存在性.对波的相互作用以及扰动波在主激波和活塞上的反射作出了精确的估计,在对主激波的强度不加限制的情况下证明了激波解的整体存在性.     

Stability of a Mach configuration

We prove the stability of a Mach configuration, which occurs in shock reflection off an obstacle or shock interaction in compressible flow. The compressible flow is described by a full, steady Euler system of gas dynamics. The unperturbed Mach configuration is composed of three straight shock lines and a slip line carrying contact discontinuity. Among four regions divided by these four lines in the neighborhood of the intersection, two are supersonic regions, and other two are subsonic regions. We prove that if the constant states in the supersonic regions are slightly perturbed, then the structure of the whole configuration holds, while the other two shock fronts and the slip line, as well as the flow field in the subsonic regions, are also slightly perturbed. Such a conclusion asserts the existence and stability of the general Mach configuration in shock theory. In order to prove the result, we reduce the problem to a free boundary value problem, where two unknown shock fronts are free boundaries, while the slip line is transformed to a fixed line by a Lagrange transformation. In the region where the solution is to be determined, we have to deal with an elliptic‐hyperbolic composed system. By decoupling this system and combining the technique for both hyperbolic equations and elliptic equations, we establish the required estimates, which are crucial in the proof of the existence of a solution to the free boundary value problem. © 2005 Wiley Periodicals, Inc.     

2D simulation of fluid-structure interaction using finite element method

This paper deals with pressure-based finite element analysis of fluid–structure systems considering the coupled fluid and structural dynamics. The present method uses two-dimensional fluid elements and structural line elements for the numerical simulation of the problem. The equations of motion of the fluid, considered inviscid and compressible, are expressed in terms of the pressure variable alone. The solution of the coupled system is accomplished by solving the two systems separately with the interaction effects at the fluid–solid interface enforced by an iterative scheme. Non-divergent pressure and displacement are obtained simultaneously through iterations. The Galerkin weighted residual method-based FE formulation and the iterative solution procedure are explained in detail followed by some numerical examples. Numerical results are compared with the existing solutions to validate the code for sloshing with fluid–structure coupling.     

Remarks on the solvability of transonic flow problems

The paper is devoted to the study of the viscosity method and upwinding in the transonic flow problems. We weaken the conditions from [6,7] under which we can obtain a nonviscous compressible transonic flow as a limit of viscous solutions, if the viscosity and heat conductivity tend to zero. Further, we give the justification of the density upwinding applied often in the calculation of transonic potential flows.     

Turbulent flow computations on 3D unstructured grids

An edge-based finite element method is presented for the simulation of compressible turbulent flows on unstructured tetrahedral grids. A two equation k–ω turbulence model is employed and the standard Galerkin approach is used for spatial discretisation. Stabilisation of the resulting procedure is achieved by the addition of an appropriate diffusion. An explicit multistage time-stepping scheme is used to advance the solution in time to steady state. The performance of the algorithm is demonstrated for the simulation of a high Reynolds number transonic separated flow over a wing.     

The formulation of linear theory of a reflected shock in cylindrical geometry

In this paper we formulate the linear theory for compressible fluids in cylindrical geometry with small perturbation at the material interface. We derive the first order equations in the smooth regions, boundary conditions at the shock fronts and the contact interface by linearizing the Euler equations and Rankine-Hugoniot conditions. The small amplitude solution formulated in this paper will be important for calibration of results from full numerical simulation of compressible fluids in cylindrical geometry.     

High order Hybrid central—WENO finite difference scheme for conservation laws

In this article we present a high resolution hybrid central finite difference—WENO scheme for the solution of conservation laws, in particular, those related to shock–turbulence interaction problems. A sixth order central finite difference scheme is conjugated with a fifth order weighted essentially non-oscillatory WENO scheme in a grid-based adaptive way. High order multi-resolution analysis is used to detect the high gradients regions of the numerical solution in order to capture the shocks with the WENO scheme while the smooth regions are computed with the more efficient and accurate central finite difference scheme. The application of high order filtering to mitigate the dispersion error of central finite difference schemes is also discussed. Numerical experiments with the 1D compressible Euler equations are shown.