偏斜来流对圆柱跨声速绕流的影响

采用大涡模拟方法数值研究了偏斜角为60°的偏斜圆柱跨声速绕流.基于非偏斜圆柱跨声速绕流的实验和数值研究工作,来流Mach数取为0.75,Reynolds数取为2×105.通过与相同参数的非偏斜圆柱跨声速绕流对比,分析了偏斜来流对柱体受力和流动特性的影响.由于偏斜来流的流动控制,偏斜圆柱的阻力比非偏斜圆柱的阻力减小高达45%,而振荡力仅受到较小的抑制.偏斜圆柱流场的可压缩性被弱化,激波和小激波消失,而整体流动的模态未改变.偏斜来流使得偏斜圆柱后的剪切层变得更为稳定,进而提升柱体背压.在剪切层的初始发展阶段,剪切层的扰动涡斜脱泻模态和快速动能衰减是偏斜圆柱剪切层更为稳定的两个主要原因.     

三维可压缩Boltzmann模型及其在低Mach数湍流中的应用（英文）

改进了有限差分格子Boltzmann方法(FDLBM),以直接数值模拟气动噪声.基于LB求解器特性,采用动力学方程中的恒定对流速度以实施高阶迎风差分,提高了声波和湍流的分辨率.通过建立一个新的三维粒子模型,计算得到了任意比热容的三维可压缩Navier-Stokes系统.此外,利用Bhatnagar-Gross-Krook(BGK)碰撞算子,通过引入热流量修正,实现了Prandtl数的可变性.在激波管内弱声波以及伴随有温度梯度的Taylor-Couette层流的验证计算中,提出的新方法结果良好.此外也对NACA0012翼型绕流进行了三维模拟.其中,Reynolds数、Mach数和攻角分别取2×105,8.75×10-2以及9°.计算发现,在机翼前缘附近的分离气流位置,以及表面压力波动强度的Mach数依赖性方面,数值计算结果与实验结果相吻合.     

基于Roe格式的可压与不可压流的统一计算方法

摘要：以Navier-Stokes方程为基础，基于有限体积的时间推进的预处理技术．提出了一个可以用来求解可压与不可压流场的统一的计算方法，原始变量选用压力、速度与温度，通过矩阵变换与重构，使得对流项系数矩阵在可压与小可压条件下都不会奇异．将可压与不可压流场的计算方法统一起来。采用Roe格式计算对流通量，采用中心差分格式计算扩散通量．算例表明，该方法可以进行高Mach数、中等Mach数、低Mach数及不可压流场的计算。由于采用了Roe格式，该方法还可以捕获不连续流场的间断面。     

可压缩均匀各向同性湍流的直接数值模拟

采用8阶精度的中心差分格式及7阶精度的迎风偏斜格式对Re_l = 72~153, M_t= 0.2~0.7的均匀各向同性湍流进行了直接数值模拟, 建立了湍流数据库. 与他人的计算结果吻合十分理想, 说明方法的有效性. 数值结果表明, 采用适当的迎风型差分格式可以克服起动问题(start-up problem)对湍流Mach数的限制, 提高可计算的湍流Mach数, 是可压湍流直接数值模拟的有效方法. 分析了压缩性效应对湍流统计量的影响, 发现压缩性使得湍动能的衰减加快. 探讨了可压湍流中微激波产生的机理, 对流场进行了标度律分析. 发现在本文的Reynolds数和湍流Mach数条件下, 流场中扩展自相似性仍然成立, 同时发现压缩性对标度指数影响不大.     

三维可压缩Boltzmann模型及其在低Mach数湍流中的应用

改进了有限差分格子Boltzmann方法(FDLBM),以直接数值模拟气动噪声.基于LB求解器特性,采用动力学方程中的恒定对流速度以实施高阶迎风差分,提高了声波和湍流的分辨率.通过建立一个新的三维粒子模型,计算得到了任意比热容的三维可压缩Navier-Stokes系统.此外,利用Bhatnagar-Gross-Krook (BGK)碰撞算子,通过引入热流量修正,实现了Prandtl数的可变性.在激波管内弱声波以及伴随有温度梯度的Taylor-Couette层流的验证计算中,提出的新方法结果良好.此外也对NACA0012翼型绕流进行了三维模拟.其中,Reynolds数、Mach数和攻角分别取2× 105,8.75×10-2以及9°.计算发现,在机翼前缘附近的分离气流位置,以及表面压力波动强度的Maeh数依赖性方面,数值计算结果与实验结果相吻合.     

基于有限体积法的非结构网格大涡模拟离散方法研究

非结构网格下的大涡模拟是解决复杂几何体高Reynolds(雷诺)数流动的有效途径.首先,基于有限体积法,研究了对流项和扩散项非结构网格下的离散方法.研究结果表明:基于TVD(total variation diminishing)限制器的限制中心差分格式保证了对流项的二阶精度并抑制了非物理振荡,同时,线性迎风格式虽然稳定,但数值耗散过大,且不能保证有界,中心差分格式引起了周期性非物理振荡;扩散项的超松弛非正交修正减小了网格非正交带来的离散误差,但修正系数须根据网格非正交的程度进行合理选取.为验证所述离散方法对大涡模拟的适用性,数值计算了Re=1.14×10~6下的非定常三维小球绕流,计算方法包括:计算网格用基于Delaunay三角剖分和Netgen前沿推进算法的四面体非结构网格;湍流模型用改进的延迟分离涡大涡模型;在离散格式的选取上,对流项用限制中心差分,扩散项加入非正交修正,插值格式用最小二乘法,时间项用二阶后向差分.计算结果表明,所用离散方法稳定收敛并且与实验数据基本吻合.     

Re=3900的圆柱绕流湍流模拟对比研究

重点采用DDES和CLES研究基于Reynolds(雷诺)数3 900的圆柱绕流.大量已有实验和数值研究结果表明:圆柱后缘流动结构和回流区长度与数值空间离散格式息息相关.基于此考虑,选用了一个优化格式并通过典型的简单湍流流动和强激波流动验证了格式对多尺度结构和激波的捕捉能力.然后,分别采用DDES和CLES对基于Reynolds数3 900的圆柱进行数值模拟.通过对比圆柱表面压力分布、圆柱表面平均速度型和圆柱尾迹区的时均脉动量,发现CLES相比于DDES与实验值吻合更好.从瞬时流场来看,DDES和CLES都能捕捉丰富的流场结构,此外,CLES在物面附近区域包含更多微小脉动.最后,尽管CLES对时均脉动捕捉好于DDES,但是程序实现更加复杂.     

Re=3900的圆柱绕流湍流模拟对比研究（英文）

重点采用DDES和CLES研究基于Reynolds(雷诺)数3 900的圆柱绕流.大量已有实验和数值研究结果表明:圆柱后缘流动结构和回流区长度与数值空间离散格式息息相关.基于此考虑,选用了一个优化格式并通过典型的简单湍流流动和强激波流动验证了格式对多尺度结构和激波的捕捉能力.然后,分别采用DDES和CLES对基于Reynolds数3 900的圆柱进行数值模拟.通过对比圆柱表面压力分布、圆柱表面平均速度型和圆柱尾迹区的时均脉动量,发现CLES相比于DDES与实验值吻合更好.从瞬时流场来看,DDES和CLES都能捕捉丰富的流场结构,此外,CLES在物面附近区域包含更多微小脉动.最后,尽管CLES对时均脉动捕捉好于DDES,但是程序实现更加复杂.     

流体力学中的差分方法(Ⅳ)——低Mach数流动的数值解

在许多实际问题中,需要计算低Mach数流动。由于它是一个由抛物型方程和双曲型方程组成的非线性方程组,因此在严格估计误差时相当困难。在[2]中讨论了Navier—Stokes方程组差分解的某些理论问题,在[3]中把此方法应用到低Mach数流动,但只限于最简单的情况。本文中较系统地讨论了这一问题,其中包括差分格式的建立,周期解问题的计算稳定性,多步格式的优越性及边值误差的影响,等等。     

增强可压缩混合层混合的一种方法

通过数值模拟的方法,研究在二维可压缩混合层的低速入口部分强迫流向流速振荡,以探讨是否有可能提高可压缩混合层的混合.对来流Mach数M=0.6的二维可压缩混合层进行系统的计算,结果证实了这种方法确实可以提高混合的效率.     

An implicit finite volume method for the solution of 3D low Mach number viscous flows using a local preconditioning technique

This paper presents a cell-centered high order finite volume scheme for the solution of the three-dimensional (3D) Navier–Stokes equations with low Mach number. The system of non-linear equations is solved by means of a fully implicit pseudo-transient scheme. Each pseudo-time step is solved by a Newton-GMRes procedure. A local preconditioning technique is used to scale the speed of sound and to improve the system condition number for low Mach number and low cell Reynolds number. This preconditioning is applied to the AUSM+up flux vector splitting function. The method is tested on 2D and 3D low Mach number laminar flows.     

Viscous fluid flow at all speeds: analysis and numerical simulation

In [43] a finite volume method for reliable simulations of inviscid fluid flows at high as well as low Mach numbers based on a preconditioning technique proposed by Guillard and Viozat [14] is presented. In this paper we describe an extension of the numerical scheme for computing solutions of the Euler and Navier-Stokes equations. At first we show the high resolution properties, accuracy and robustness of the finite volume scheme in the context of a wide range of complicated transonic and supersonic test cases whereby both inviscid and viscous flow fields are considered. Thereafter, the validity of the method in the low Mach number regime is proven by means of an asymptotic analysis as well as numerical simulations. Whereas in [43] the asymptotic analysis of the scheme is focused on the behaviour of the continuous and discrete pressure distribution for inviscid low speed simulations we prove both the physical sensible discrete pressure field for viscous low Mach number flows and the divergence free condition of the discrete velocity field in the limit of a vanishing Mach number with respect to the simulation of inviscid fluid flow.     

Viscous fluid flow at all speeds: analysis and numerical simulation

In [43] a finite volume method for reliable simulations of inviscid fluid flows at high as well as low Mach numbers based on a preconditioning technique proposed by Guillard and Viozat [14] is presented. In this paper we describe an extension of the numerical scheme for computing solutions of the Euler and Navier-Stokes equations. At first we show the high resolution properties, accuracy and robustness of the finite volume scheme in the context of a wide range of complicated transonic and supersonic test cases whereby both inviscid and viscous flow fields are considered. Thereafter, the validity of the method in the low Mach number regime is proven by means of an asymptotic analysis as well as numerical simulations. Whereas in [43] the asymptotic analysis of the scheme is focused on the behaviour of the continuous and discrete pressure distribution for inviscid low speed simulations we prove both the physical sensible discrete pressure field for viscous low Mach number flows and the divergence free condition of the discrete velocity field in the limit of a vanishing Mach number with respect to the simulation of inviscid fluid flow.     

A low-Mach number method for the numerical simulation of complex flows

A new numerical procedure which considers a modification to the artificial acoustic stiffness correction method (AASCM) is here presented, to perform simulations of low Mach number flows with the compressible Navier–Stokes equations. An extra term is added to the energy fluxes instead of using an energy source correction term as in the original model. This new scheme re-scales the speed of sound to values similar to the flow velocity, enabling the use of larger time steps and leading to a more stable numerical method. The new method is validated performing Large Eddy Simulations on test problems. The effect of a crucial numerical parameter alpha is evaluated as well as the robustness of the method to variations of the Mach number. Numerical results are compared to the existing experimental data showing that the new method achieves good agreement increasing the time-step, and therefore accelerating the computation for low-Mach convective flows.     

Asymptotic Expansions and Numerical Methods for Compressible and Low Mach Number Fluid Flow

The results of a formal asymptotic low Mach number analysis [5, 6] of the Euler equations of gas dynamics are used to extend the validity of a numerical method from the simulation of compressible inviscid flow fields to the low Mach number regime. Although, different strategies are applicable [7, 8, 5, 9] in this context we focus our view to a preconditioning technique recently proposed by Guillard and Viozat [16]. We present a finite volume approximation of the governing equations using a Lax‐Friedrichs scheme whereby a preconditioning of the incorporated numerical dissipation is employed. A discrete asymptotic analysis proves the validity of the scheme in the low Mach number regime.     

On Low Mach Number Preconditioning of Finite Volume Schemes

A finite volume method for inviscid unsteady flows at low Mach numbers is studied. The method uses a preconditioning of the dissipation term within the numerical flux function only. It can be observed by numerical experiments, as well as by analysis, that the preconditioned scheme yields a physically corrected pressure distribution and combined with an explicit time integrator it is stable if the time step Δt satisfies the requirement to be 𝒪(M ²) as the Mach number M tends to zero, whereas the corresponding standard method remains stable up to Δt = 𝒪(M ),M → 0, though producing unphysical results. (© 2005 WILEY-VCH Verlag GmbH & Co. KGaA, Weinheim)     

Improving shock-free compressible RANS solvers for LES on unstructured meshes

Standard numerical methods used to solve the Reynolds averaged Navier–Stokes equations are known to be too dissipative to carry out large eddy simulations since the artificial dissipation they introduce to stabilize the discretization of the convection term usually interacts strongly with the subgrid scale model. A possible solution is to resort to non-dissipative central schemes. Unfortunately, these schemes are in general unstable. A way to reach stability is to select a central scheme that conserves the discrete kinetic energy. To that purpose, a family of kinetic energy conserving schemes is developed to perform simulations of compressible shock-free flows on unstructured grids. A direct numerical simulation of the flow past a sphere at a Reynolds number of 300 and a large eddy simulation at a Reynolds number of 10,000 are performed to validate the methodology.     

An improved AUSM-family scheme with robustness and accuracy for all Mach number flows

With the increasing popularity of Computational Fluid Dynamics (CFD), the reliability of numerical scheme becomes prominent. The work presents a newly improved scheme more reliable in all Mach number regimes to circumvent some typical symptoms of the previous AUSM-family schemes observed in hypersonic and very low speeds. This scheme is facilitated by reconstructing pressure diffusion term in mass flux, velocity diffusion term in pressure flux and numerical sound speed. Then, a variety of benchmark test cases are selected to systematically assess the effects of these key ingredients and investigate the additional features in terms of robustness and accuracy. The proposed scheme attains stronger shock robustness against carbuncle instability, better low-speed accuracy and higher resolution of oblique shocks compared with many existing upwind schemes. Moreover, it can exactly resolve contact discontinuity, preserve positivity, damp numerical overshoots and avert the global cut-off strategy. Numerical results for a wide spectrum of Mach numbers indicate its potential and reliable application to all Mach number flows.     

A Roe-type scheme with low Mach number preconditioning for a two-phase compressible flow model with pressure relaxation

We describe two-phase compressible flows by a hyperbolic six-equation single-velocity two-phase flow model with stiff mechanical relaxation. In particular, we are interested in the simulation of liquid-gas mixtures such as cavitating flows. The model equations are numerically approximated via a fractional step algorithm, which alternates between the solution of the homogeneous hyperbolic portion of the system through Godunov-type finite volume schemes, and the solution of a system of ordinary differential equations that takes into account the pressure relaxation terms. When used in this algorithm, classical schemes such as Roe’s or HLLC prove to be very efficient to simulate the dynamics of transonic and supersonic flows. Unfortunately, these methods suffer from the well known difficulties of loss of accuracy and efficiency for low Mach number regimes encountered by upwind finite volume discretizations. This issue is particularly critical for liquid-gasmixtures due to the large and rapid variation in the flow of the acoustic impedance. To cure the problem of loss of accuracy at low Mach number, in this work we apply to our original Roe-type scheme for the two-phase flow model the Turkel’s preconditioning technique studied by Guillard–Viozat [Computers & Fluids, 28, 1999] for the Roe’s scheme for the classical Euler equations.We present numerical results for a two-dimensional liquid-gas channel flow test that show the effectiveness of the resulting Roe-Turkel method for the two-phase system.