基于自适应直角网格的二维全速势方程有限体积解法A finite volume method for 2D Full-Potential equation on adaptive Cartesian grids

为满足亚声速和跨声速飞机概念设计中快速气动计算的需求,研究和发展一种基于自适应直角网格的非线性全速势方程有限体积解法。要点如下。（1）在几何自适应直角网格的基础上,使用结合单元融合的网格切割算法处理物面边界,提出一种修正非贴体切割网格的方法。（2）采用隐式格式结合GM RES算法求解该非线性位流方程,针对流场的自适应来捕捉激波。（3）采用镜像法处理物面边界处的无穿透条件,并提出解析的方法来修正镜像单元的值。（4）针对直角网格的特点,提出在库塔线上插入库塔单元的方法施加库塔条件。NACA0012翼型绕流的算例结果表明,该方法用于亚声速和跨声速气动计算能得到令人满意的结果,且自动化程度高、收敛速度快。     

基于自适应直角网格的二维全速势方程有限体积解法

为满足亚声速和跨声速飞机概念设计中快速气动计算的需求,研究和发展一种基于自适应直角网格的非线性全速势方程有限体积解法。要点如下。(1)在几何自适应直角网格的基础上,使用结合单元融合的网格切割算法处理物面边界,提出一种修正非贴体切割网格的方法。(2)采用隐式格式结合GMRES算法求解该非线性位流方程,针对流场的自适应来捕捉激波。(3)采用镜像法处理物面边界处的无穿透条件,并提出解析的方法来修正镜像单元的值。(4)针对直角网格的特点,提出在库塔线上插入库塔单元的方法施加库塔条件。NACA0012翼型绕流的算例结果表明,该方法用于亚声速和跨声速气动计算能得到令人满意的结果,且自动化程度高、收敛速度快。     

基于复合叉树的自适应笛卡尔网格应用研究

采用复合叉树自适应笛卡尔网格和有限体积法求解三维Euler方程,在网格生成过程中,以模型几何外形、模型表面曲率为基础,构建了基于复合叉树的网格生成和加密方法。在流场计算过程中,又针对流场变化特征,建立了基于复合叉树的网格各向异性拆分模式,同时采用以中心差分为基础的Jameson有限体积法。通过对M6机翼在跨音速情况下的数值仿真,表明计算结果与风洞实验结果符合良好,同时也表明本算法具有高分辨率、节省机时,提高计算效率等特点。     

基于分区拼接网格技术高升力装置流场数值模拟

针对高升力装置构型模型结构复杂、流场变化剧烈等特点,本文采用分区拼接网格的思想分别按照流场和结构拓扑特点对高升力装置进行了网格分区。在分区的基础上逐块生成网格,减小了增升装置网格的生成难度,提高了网格质量,减少了网格数目。首先,研究了高升力装置的分区策略及流场特点;接着以MD30P-30N多段翼型为研究算例研究了网格比例和插值方法对计算结果的影响。经过分析对比可知:外部区域与近壁区域之间的比例不宜小于1:5;内部域网格比例不宜超过1:1.8,最好保持在1:1左右;计算中应该采用高阶精度插值以保证计算精度。采用某四段翼型进行了验证;最后采用NASA标准高升力装置进行了三维高升力装置流场数值模拟并与相应风洞实验数据及对接网格计算结果进行了比较与分析,验证了拼接网格技术的高效性与可靠性。同时分析研究了绕三维增升装置的流动及其周围复杂的粘性流动现象。     

二维自适应非结构网格DSMC并行算法研究

研究了二维自适应非结构网格DSMC并行算法实现的过程.首先提出了一类非结构网格自适应策略,有效降低了网格尺度对计算结果的影响,提高了流场的分辨率;然后基于PC-CLUSTER群机并行体系结构与消息传递库MPI并行环境,利用分区并行思想,设计了非结构网格DSMC并行算法,节约了计算时间.利用For-tran90的动态分配内存技术编制了通用计算程序;最后对过渡流域高超声绕流进行了数值模拟,计算结果初步验证了算法的可行性与有效性.     

含化学反应膛口流场的无网格数值模拟

基于无网格方法,对包含大位移运动边界和非平衡化学反应的膛口流场进行了数值模拟。所发展算法是基于线性基函数最小二乘显式无网格方法,忽略黏性及湍流的影响,对流场采用ALE(arbitrary Lagrangian-Eulerian)形式的Euler方程描述,对流通量和化学反应源项采用多组分HLLC(Harten-Lax-van Leer-Contact)格式和有限速率反应模型计算,对于运动边界造成的点云畸形采用局部点云重构方法处理,重构过程中采用虚拟边阵面推进。对圆柱绕流和激波诱导燃烧流场进行了数值模拟,验证了重构方法和化学反应计算的有效性。最后对12.7 mm口径机枪膛口流场进行了模拟,结果同实验照片、非结构网格方法结果吻合较好,数值结果清晰地再现了膛口初始冲击波、膛口冲击波、欠膨胀射流波系结构的动力学发展过程,以及膛口焰的时间、空间分布特征。     

非结构隐式方法在空心弹丸流场模拟中的应用

采用非结构网格的LU-SGS隐式算法计算三维Euler方程,数值模拟了不同马赫数以及不同攻角下某空心弹丸绕流流场,分析了流场的波系结构及其升阻力特性,计算结果表明空心弹丸的阻力系数比同口径的普通弹丸的阻力系数大约小30％,空心弹丸的阻力系数以及升力系数随攻角的变化规律与普通弹丸一致．     

线化欧拉方程的高阶间断有限元数值解法研究

采用高阶间断有限元法于非结构网格上针对复杂外形数值求解声学控制方程------线化欧拉方程. 背景流场采用有限体积法于结构网格求得, 一种高精度数据传递方法将基于有限体积法的背景流场数据传递到声场计算所采用的较为稀疏的非结构网格上, 保证了背景流场信息的完整和精确. 为提高计算效率, 采用了一种更为直接的Quadrature-FreeImplementation技术以及网格分区并行技术. 数值结果表明采用高阶的情况下即使在稀疏的网格上也可以捕捉到细微的声场结构.      

非结构隐式LU-SGS方法在空心弹丸流场数值模拟中的应用

采用非结构网格的LU-SGS隐式算法计算三维Euler方程，数值模拟了不同 马赫数以及不同攻角下某空心弹丸绕流流场，分析了流场的波系结构及其升阻力特性，计算 结果表明空心弹丸的阻力系数比同口径的普通弹丸的阻力系数大约小30{\%}，空心弹丸的 阻力系数以及升力系数随攻角的变化规律与普通弹丸一致.     

基于Navier-Stokes／Kirchhoff方程的悬停旋翼跨声速气动声学计算

研究了Kirchhoff积分面是否有盖有底,以及是否计及旋翼网格上的流场值,这两个因素对噪声预测结果的影响.发展了一种基于重叠网格的计算悬停旋翼远场噪声的数值方法.数值计算过程分为流场模拟和声场模拟两部分.悬停旋翼流场的数值模拟是在两个相互重叠的网格上进行的:在高质量的旋翼网格上求解Navier-Stokes方程,用于模拟旋翼附近的粘性流动和近场尾涡的捕捉;在远离粘性区域处布置符合悬停流场物理特征的圆柱形背景网格,控制方程为Euler方程,用于远场尾涡的捕捉.计算得到的流场信息插值到用于声场计算的Kirchhoff积分面上.观测点处的噪声可以认为是由这个完全包含桨叶的Kirchhoff积分面上的面元(声源)发声得到.远场声波的传播由Kirchhoff积分公式描述.计算结果表明:采用有盖有底的Kirchhoff积分面并且同时计及旋翼网格流场值时,计算得到的HSI噪声与实验值吻合最好.     

An unstructured/structured multi‐layer hybrid grid method and its application

A multi‐layer hybrid grid method is constructed to simulate complex flow field around 2‐D and 3‐D configuration. The method combines Cartesian grids with structured grids and triangular meshes to provide great flexibility in discretizing a domain. We generate the body‐fitted structured grids near the wall surface and the Cartesian grids for the far field. In addition, we regard the triangular meshes as an adhesive to link each grid part. Coupled with a tree data structure, the Cartesian grid is generated automatically through a cell‐cutting algorithm. The grid merging methodology is discussed, which can smooth hybrid grids and improve the quality of the grids. A cell‐centred finite volume flow solver has been developed in combination with a dual‐time stepping scheme. The flow solver supports arbitrary control volume cells. Both inviscid and viscous flows are computed by solving the Euler and Navier–Stokes equations. The above methods and algorithms have been validated on some test cases. Computed results are presented and compared with experimental data. Copyright © 2006 John Wiley & Sons, Ltd.     

Automatic grid generation of complex geometries in Cartesian co-ordinates

A method of automatic grid generation for complex boundaries in Cartesian co-ordinates is proposed in this paper. In addition to the Cartesian grid lines the diagonal segments are used for the approximations of complex geometries in Cartesian co-ordinates. A structured Cartesian grid is employed for the sake of the numerical simplicity and the potential of automatic grid generation. The automatic grid generation is achieved by this diagonal Cartesian method and the accuracy estimations of geometry approximations are given. The approximations of a few complex geometries, such as the multibody system in porous media, lake banks, grooved channels and spheres are shown and analyzed. The proposed method is verified by the numerical solutions of a rotated cavity flow. It is shown that the diagonal Cartesian method improves both the accuracy of geometry approximations and the numerical solution of a rotated cavity flow, comparing with the traditional saw-tooth method in which only Cartesian grid lines are utilized for geometry approximations. The stability and convergence of the proposed method is demonstrated. Finally, the application of the diagonal Cartesian method for the prediction of a grooved channel flow is presented. © 1998 John Wiley & Sons, Ltd.     

Adaptive Runge–Kutta discontinuous Galerkin method for complex geometry problems on Cartesian grid

A Cartesian grid method using immersed boundary technique to simulate the impact of body in fluid has become an important research topic in computational fluid dynamics because of its simplification, automation of grid generation, and accuracy of results. In the frame of Cartesian grid, one often uses finite volume method with second order accuracy or finite difference method. In this paper, an h‐adaptive Runge–Kutta discontinuous Galerkin (RKDG) method on Cartesian grid with ghost cell immersed boundary method for arbitrarily complex geometries is developed. A ghost cell immersed boundary treatment with the modification of normal velocity is presented. The method is validated versus well documented test problems involving both steady and unsteady compressible flows through complex bodies over a wide range of Mach numbers. The numerical results show that the present boundary treatment to some extent reduces the error of entropy and demonstrate the efficiency, robustness, and versatility of the proposed approach. Copyright © 2013 John Wiley & Sons, Ltd.     

翼吊式双发民机机体/动力装置一体化数值分析

介绍了多块网格技术与流场分区求解方法在翼吊式双发民机机体／动力装置一体化研究中的应用。数值求解Ｅｕｌｅｒ方程模拟复杂组合体绕流。采用边界层方程／Ｅｕｌｅｒ方程耦合迭代技术进行翼面粘性修正。为保持Ｅｕｌｅｒ注解中计算网格固定,粘流／无粘流耦合迭采用表面源模型。该方法对某民用飞机模型跨音速绕流流场进行了数值模拟,机翼表面计算压力分布与实验吻合良好。     

A method for generating irregular computational grids in multiply connected planar domains

A method for generating irregular triangular computational grids in two-dimensional multiply connected domains is described. A set of points around each body is defined using a simple grid generation technique appropriate to the geometry of each body. The Voronoi regions associated with the resulting global point distribution are constructed from which the Delaunay triangulation of the set of points is thus obtained. The definition of Voronoi regions ensures that the triangulation produces triangles of reasonable aspect ratios given a grid point distribution. The approach readily accommodates local clustering of grid points to facilitate variable resolution of the domain. The technique is generally applicable and has been used with success in computing triangular grids in multiply connected planar domains. The suitability of such grids for flow calculations is demonstrated using a finite element method for solution of the inviscid transonic flow over two- dimensional high-lift aerofoil configurations.     

一种分子运动和碰撞双重网格DSMC方法研究

基于非结构网格与直角网格相结合的策略,提出一种分子运动和碰撞双重网格DSMC实现方法。通过分子的位置坐标信息,实现运动网格与碰撞网格信息交互,从而结合非结构网格的贴体性和直角网格易于控制子网格数量的优点,同时提出并实现了基于MCS自适应的动态子网格技术以有效限制分子平均碰撞距离,提高了DSMC方法的通用性和计算精度。通过对超声速圆柱绕流和扩张管道的数值模拟,验证该方法的有效性和高精度性。数值结果表明,本文提出的基于分子运动和碰撞双重网格的DSMC方法提高了流场的分辨率,且通过基于MCS自适应的动态子网格技术,有效地降低了流场的平均碰撞距离,提高了碰撞质量和计算精度。     

带有襟翼偏转的三维机翼绕流的N—S方法解

给出了带襟翼偏转的三维机翼绕流的一种求解Ｎ－Ｓ方程的计算方法,采用区域求解算法和对接分区网络技术相结合的方法,有效地求解了绕此外形的复杂流动,区域求解算法中提出了一种满足通量守恒的内边界耦合条件,流场求解时采用中心差分的限体积方法对空间通量顶进行离散,采用显式推进方法进行时间方向的积分,数值算例表明本方法是求解带襟翼偏转的机翼绕流的有效方法。     

Euler solution using adaptive Cartesian grid with a gridless boundary treatment

A quadtree-based adaptive Cartesian grid generator and flow solver were developed. The grid adaptation based on pressure or density gradient was performed and a gridless method based on the least-square fashion was used to treat the wall surface boundary condition, which is generally difficult to be handled for the common Cartesian grid. First, to validate the technique of grid adaptation, the benchmarks over a forward-facing step and double Mach reflection were computed. Second, the flows over the NACA 0012 airfoil and a two-element airfoil were calculated to validate the developed gridless method. The computational results indi- cate the developed method is reasonable for complex flows.     

A numerical study on a Cartesian-based body-fitted adaptive grid method

ABSTRACT

A hybrid Cartesian-based body-fitted adaptive grid method for compressible Navier–Stokes equations is implemented and investigated. In this method, the body-fitted structured grids are generated around the geometries, and the left regions are filled with Cartesian grids. To transfer the data between the different grids, the donor cell searching technique is adopted. An unstructured data-based finite volume update procedure is used, and least squares method is suggested to retain the second order in the overlap region. The moving shock waves with different speeds and vortex passing through the interfaces of the hybrid Cartesian grid are used to explore the accuracy and conservation. A new technique is presented to deal with the non-physical stagnation of slowly moving shock wave around the interface of grid. Numerical examples are presented to demonstrate the results. The three-dimensional extension has also been shown by a benchmark problem.