黏性边界层网格自动生成

高雷诺数黏性流动在壁面附近存在边界层,在计算模拟中自动生成可靠且有效的计算网格仍然是计算流体力学存在的瓶颈.三棱柱/四面体混合网格技术在一定程度上缓解了这个困难.然而,对于复杂外形的情况,在边界层内自动高效生成高质量的三棱柱单元仍然十分困难.常用的层推进法在凹凸区域及角点处生成的边界层网格单元质量较差,边界层网格最外层尺寸不均匀.针对这些问题,发展了一种黏性边界层网格自动生成方法,通过顶点周围边的二面角识别物面网格特征确定多生长方向,预估并调整生长高度处理相交情况.同时提出一种三维前沿尺寸调节方式,提高了边界层网格单元的正交性,保证了边界层网格与远场网格尺寸的光滑过渡.通过ONERA M6翼型以及带发动机短舱的DLR-F6翼身组合体等外形的网格生成实例及绕流数值模拟,将计算值与标准实验值进行对比,结果表明:该方法能够自动高效地生成满足数值计算需求的混合网格.     

一种基于双前沿推进的边界层网格生成算法

高雷诺数粘性流动模拟对边界层内的网格正交性有特殊要求.对于复杂外形,这类问题的网格自动化生成十分困难.面向该问题,提出一种双前沿推进思想,并形成一种面向复杂几何外形的边界层网格全自动生成算法.结合多种网格技术处理局部几何特征以保证边界层网格的质量.双前沿推进思想同时适用于多块结构网格和混合网格的边界层网格生成.多个模型...     

层裂问题的交错网格物质点法研究

交错网格物质点法(Staggered Grid Material Point Method,SGMP)有效地消除了物质点法(Material Point Method,MPM)的跨网格数值误差,是模拟冲击爆炸等涉及大变形与材料破坏问题的一种有效数值分析方法.为了研究层裂问题,论文将质点失效模型引入交错网格物质点法中,对...     

一种快速稳健的并行多块结构动网格方法

为解决传统网格处理方法不能满足复杂外形在大设计空间内进行优化时对网格质量的要求的问题,提出了一种并行多块动网格方法,该方法基于初始外形的多块结构网格,根据优化过程中个体外形与初始外形拓扑结构相近的特性,利用体样条插值方法来拟合多块结构网格各块顶点的位移,得到几何外形变化后的拓扑结构,再利用无限插值方法并行地移动初始外形多块结构网格的边、面和块内的网格点,进行光顺处理后得到变形后几何外形的空间网格;该方法在保证网格质量的同时,可以极大地提高网格生成效率,本文以某翼身组合体为例结果表明,该方法在大设计空间的复杂外形设计问题中具有很强的实用性。     

适应复杂外形的三维粘性混合网格生成算法

提出一类适应复杂外形的粘性混合网格生成算法。表面网格由前沿推进三角形曲面网格程序获得,边界层布置各向异性的三棱柱体网格,远物面区域采用Delaunay方法生成四面体网格。针对模型的复杂几何特征,综合采用了各种网格处理技术,以保证边界层网格的质量,并避免算法失效问题。网格实例及计算结果表明了本文算法的实用性及和效性。     

弹性薄板的广义多维微分求积分析方法

多维微分求积DC(differential cubature)法是近年迅速发展起来的一种处理多维微分方程的高精度数值方法。本文围绕多元函数插值适定性这一基本问题,探讨了实现DC法时插值结点组和插值空间应满足的条件,研究了离散结点组选择及其构造适定试函数的方法。提出了一种沿各坐标方向可以布置不同数量结点的广义交错网格DC方法,并给出了确定相应的插值空间及其选择试函数的具体方案。通过弹性薄板变形分析研究了广义交错网格DC法解决实际结构力学问题的可靠性及其潜力。研究结果表明,广义交错网格DC法较传统的交错网格DC格式具有更强的适用性和灵活性,采用数量少得多的离散结点即可达到传统交错网格DC法相同的数值精度,表现出精度高和计算工作量小的优点。     

不同网格拓扑对细长体绕流计算的影响研究

分别运用扇形(Fan)、阶梯形(Ladder)、交界面形(Interface)网格对细长体小攻角对称、大攻角对称、大攻角非对称绕流流场进行了数值研究．通过涡核位置、涡簇显示、物面压力分布、轴向力分布等的计算结果比较了三种网格的计算精度．数值实验表明：细长体分离涡流场对边界层网格非常敏感,应严格控制边界层网格的正交性;随着攻角增大,流场对网格特性的敏感性有增高的趋势;阶梯形网格可能会对流场带入非物理性扰动,交界面网格对流场捕捉有不连续现象;将三种网格得到的物面压力、侧向力、流动分离位置与实验值进行对比,发现扇形网格误差最小、交界面网格误差最大;大攻角非对称流动时,扇形网格计算的侧向力有整体向细长体头部压缩的趋势,涡脱落位置靠前,第二个及第三个极值更大,说明非对称现象有向尾部发展的趋势．     

基于二重网格的动网格松弛法改进

相比传统的弹簧法等方法,基于球松弛算法的动网格松弛法在复杂边界大变形条件下可以得到质量更高的边界网格以及更大的极限变形量,但该方法在时间效率上还有提升的空间.引入二重网格,采用动网格松弛法进行稀疏网格的网格变形,将边界位移传递到整个网格计算域;再利用二重网格映射,将稀疏网格位移映射到原有计算网格的节点上.算例表明,改进...     

静气动弹性计算方法研究

对基于结构网格的Euler方程及N-S方程求解器和基于非结构网格的Euler方程求解器,采用结构模态分析方法和柔度矩阵方法,对无人机大展弦比机翼在Ma=0.6,α=2?, 飞行高度20km的巡航状态下的静气动弹性特性进行了数值模拟. 验证了两种求解器对静气动弹性模拟的准确性. 同时,对模态分析方法和柔度矩阵方法进行了对比研究,发现柔度矩阵方法更适用于静气动弹性数值模拟. 另外,对应用物面法向偏转方法替代网格变形技术模拟静气动弹性进行了研究,计算表明物面法向偏转方法可以大大提高静气动弹性计算效率和克服机翼结构变形过大时动网格技术无法处理的不足.      

非结构混合网格在气动热标模模拟中的应用

非结构混合网格消除了结构网格节点的结构性限制,可以较好地处理边界,同时兼顾了粘性边界层模拟的需求,具有灵活性大、对复杂外形适应能力强和生成耗时短等优点,在飞行器气动特性模拟中得到广泛应用.本文针对非结构混合网格的特点,把前期针对非结构混合网格气动力高精度模拟发展改进的梯度计算方法和Roe格式熵修正方法推广应用到气动热流的数值模拟.以典型钝锥标模外形的高超声速绕流为研究对象,开展了不同网格形式和第一层网格不同间距的影响研究.结果 表明,热流计算时,头部物面网格最好采用四边形或四边形交叉剖分得到的三角形网格,物面法向的网格雷诺数取20左右,为热流计算时非结构混合网格的生成提供了指导,同时验证了计算方法的有效性和可靠性.     

Developing a new mesh deformation technique based on support vector machine

Mesh deformation technique is widely applied in numerical simulations involving moving boundaries, and the deforming capability and efficiency is the key of it. In this paper, we present a new point-by-point mesh deformation method based on the support vector machine. This proposed method, to certain extent, is similar to the radial basis function (RBF) interpolation method with data reduction, but the new approach selects key boundary points automatically without specifying an initial set, and the function coefficients are obtained by solving a simple quadratic programming problem. Therefore, it is more efficient than the RBF method. Typical 2D/3D applications and realistic unsteady flow over a pitching airfoil are simulated to demonstrate the capability of the new method. With proper setting, the quality of the deformed meshes after using the new method is comparable to that of the RBF method, and the performance is improved by up to 7 ×.     

Mesh deformation based on artificial neural networks

In the article a new mesh deformation algorithm based on artificial neural networks is introduced. This method is a point-to-point method, meaning that it does not use connectivity information for calculation of the mesh deformation. Two already known point-to-point methods, based on interpolation techniques, are also presented. In contrast to the two known interpolation methods, the new method does not require a summation over all boundary nodes for one displacement calculation. The consequence of this fact is a shorter computational time of mesh deformation, which is proven by different deformation tests. The quality of the deformed meshes with all three deformation methods was also compared. Finally, the generated and the deformed three-dimensional meshes were used in the computational fluid dynamics numerical analysis of a Francis water turbine. A comparison of the analysis results was made to prove the applicability of the new method in every day computation.     

Hybrid grid generation for viscous flow analysis

Cartesian grid with cut‐cell method has drawn attention of CFD researchers owing to its simplicity. However, it suffers from the accuracy near the boundary of objects especially when applied to viscous flow analysis. Hybrid grid consisting of Cartesian grid in the background, body‐fitted layer near the object, and transition layer connecting the two is an interesting alternative. In this paper, we propose a robust method to generate hybrid grid in two‐dimensional (2D) and three‐dimensional (3D) space for viscous flow analysis. In the first step, body‐fitted layer made of quadrangles (in 2D) or prisms (in 3D) is created near the object's boundary by extruding front nodes with a speed function depending on the minimum normal curvature obtained by quadric surface fitting. To solve global interferences effectively, a level set method is used to find candidates of colliding cells. Then, axis‐aligned Cartesian grid (quadtree in 2D or octree in 3D) is filled in the rest of the domain. Finally, the gap between body‐fitted layer and Cartesian grid is connected by transition layer composed of triangles (in 2D) or tetrahedrons (in 3D). Mesh in transition layer is initially generated by constrained Delaunay triangulation from sampled points based on size function and is further optimized to provide smooth connection. Our approach to automatic hybrid grid generation has been tested with many models including complex geometry and multi‐body cases, showing robust results in reasonable time. Copyright © 2012 John Wiley & Sons, Ltd.     

A new mesh relaxation approach and automatic time‐step control method for boundary integral simulations of a viscous drop

We present a numerical methodology for the simulation of a viscous drop under simple shear flows by using the boundary integral method. The present work treats only a single drop in an unbounded fluid‐flow, but the results can be directly applied to studies on the rheology of dilute emulsions, in which the hydrodynamic interactions between two or more drops can be neglected. Singular and non‐singular integral representations of the velocity field are considered. Several aspects of the method are presented, including a new mesh relaxation approach and an automatic time‐step control method. The relaxation strategy is used in order to contain the distortion of the mesh and is performed by using relaxation iterations in a virtual temporal march between each physical time step of the simulation and monitoring the standard deviation of the areas of the elements. The automatic time‐step control method uses a global quantity related to the drop deformation in order to automatically set the temporal integration time step. It is carried out in a way to keep the local integration error less than a given tolerance. This strategy reduces the computational cost of the simulation by dramatically reducing the number of time steps in the temporal integration process. Copyright © 2016 John Wiley & Sons, Ltd.     

基于网格框架的非结构附面层网格生成技术

附面层网格质量是确保计算流体力学粘性计算精度的关键技术环节.本文针对复杂外形提出了全局一致的高质量附面层网格构造算法,该方法基于针对特征的表面网格区域分解技术,利用表面网格分片后的边界线及其法向量构造最终附面层网格的轮廓框架线,并通过径向基函数及线性插值算法生成完整的附面层网格.通过典型算例分析可以看出,该方法生成的非结构附面层网格精度和全局一致性较高,且能够有效避免复杂外形附面层网格局部及全局交叉现象.     

Mesh Deformation Method Based on Mean Value Coordinates Interpolation

Mesh deformation technique is widely used in many application fields, and has received a lot of attentions in recent years. This paper focuses on the methodology and algorithm of algebraic type mesh deformation for unstructured mesh in numerical discretization. To preserve mesh quality effectively, an algebraic approach for two and three dimensional unstructured mesh is developed based on mean value coordinates interpolation combined with node visibility analysis.The proposed approach firstly performs node visibility analysis to find out the visible boundary for each grid point to be moved, then evaluates the mean value coordinates of each grid point with respect to all vertices on its visible boundary. Thus the displacements of grid points can be calculated by interpolating the boundary movement by the mean value coordinates. Compared with other methods, the proposed method has good deformation capability and predictable computational cost, with no need to select parameters or functions. Applications of mesh deformation in different fields are presented to demonstrate the effectiveness of the proposed approach. The results of numerical experiments exhibit not only superior deformation capability of the method in traditional applications of fluid dynamic grid, but also great potential in modeling for large deformation analysis and inverse design problems.     

Mesh adaptation as a tool for certified computational aerodynamics

Mesh convergence order is a key for certification of the accuracy of numerical solutions. A few available results and tools in mesh adaption are synthetized in order to specify a mesh converging method for adaptive calculation of compressible flows including shocks or viscous layers. The main design property for this method is early second‐order convergence, where early means that the second‐order convergence is obtained with coarse meshes. Copyright © 2004 John Wiley & Sons, Ltd.