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.     

绕翼身组合体高质量网格设计和阻力计算

采用超立方体概念设计了绕翼身组合体外形的高质量连续拼接多块结构化网格,旨在构造一种通用的绕翼身组合体外形的高质量网格生成方法,提高阻力计算精度.以DLR-F4翼身组合体为例生成计算网格,采用雷诺平均Navier-Stokes方程耦合Spalart-Allmaras 湍流模型进行阻力计算.超立方体网格计算的结果与实验数据吻合较好,优于其他软件和其他网格的计算结果;从而说明本文超立方体网格构建方法可行、生成的网格质量高,能改善阻力精度,该方法适用于绕相似外形的翼身组合体网格生成.     

复杂外形飞行器压力分布CFD数值模拟与试验结果比较

为观察粘性效应对物面压力分布的影响,并验证 CFD 数值模拟方法的计算结果,设计了翼-身-舵组合体模型,利用航天空气动力技术研究院的FD-20炮风洞,在马赫数Ma分别取6、8且攻角α分别取0o、10o、20o的条件下进行了风洞测压试验,同时用Euler方程和N-S方程计算了模型的表面压力并与试验结果进行了比较。结果表明：除少数测点外,弹身、弹翼、舵面及弹身-弹翼干扰区的 Euler方程和 N-S方程计算结果都比较一致,除了攻角α=20°时的弹翼外,计算结果都与试验结果吻合较好。攻角α=20°的极小展弦比三角弹翼,由于侧前缘脱涡等分离现象的存在,实验值普遍高于计算值10%～15%,但变化趋势一致。因此,在采用CFD数值模拟与工程计算相结合的方法进行气动加热或非定常气动力的计算中,采用Euler方程代替N-S方程求解边界层外缘参数和当地流参数是合理的。     

机翼-机身-挂架-短舱复杂流场数值模拟

本文采用分区搭接网格技术,对机翼/机身/挂架/短舱复杂组合体进行网格分布,通过分析计算网格对结果的影响,探讨了网格的划分.基于Roe的近似黎曼解的方法,采用S-A湍流模型,通过求解N-S方程,对该组合体外流场/发动机短舱内流场进行一体化数值模拟,与相应风洞实验数据进行了比较与分析,取得了与实验数据较为吻合的结果.与无发动机短舱的组合体的气动特性进行比较,分析了短舱对翼身组合体的气动干扰.     

跨音速大迎角绕流的Euler方程数值模拟

采用保角变换与代数方法相结合，生成全场统一的贴体、正交Ｏ－Ｈ型网格．采用有限体积法求解Ｅｕｌｅｒ方程，模拟具有歼击机外形的全机及翼身组合体大迎角跨音速绕流．计算表明，法向力系数、气动中心位置及压力分布的计算结果与实验结果吻合良好     

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.     

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。     

采用自适应直角网格计算三维增升装置绕流

针对三维增升装置绕流，对存在剪刀叉的不连续外形，基于自适应直角网格，提出并介绍了分区和面搭接技术，采用变长宽比网格，进行了直角网格生成和流场Euler方程数值计算. 根据几何外形的特点，在直角网格生成过程中，以外形不连续面作为分区边界，对初始``根'网格实施分区处理，降低了整个网格的生成难度. 通过基于外形的自适应网格加密，详细描述了剪刀叉外形和缝道，提高了网格质量. 在分区边界面上，基于面搭接技术，构造重叠面积切割算法，实现边界两侧网格间的流场信息传递，保证流场计算中的通量守恒. 采用中心有限体积方法，结合双时间推进算法，完成了两段机翼、带增升襟翼翼身组合体绕流流场的Euler方程数值模拟，对计算结果与实验数据进行了对比，验证了所提方法、算法的合理性和实用性.     

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.      

西南某大型水电站拱肩槽边坡开挖的变形响应研究

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.     

CFD‐based optimization of aerofoils using radial basis functions for domain element parameterization and mesh deformation

A novel domain element shape parameterization method is presented for computational fluid dynamics‐based shape optimization. The method is to achieve two aims: (1) provide a generic ‘wrap‐around’ optimization tool that is independent of both flow solver and grid generation package and (2) provide a method that allows high‐fidelity aerodynamic optimization of two‐ and three‐dimensional bodies with a low number of design variables. The parameterization technique uses radial basis functions to transfer domain element movements into deformations of the design surface and corresponding aerodynamic mesh, thus allowing total independence from the grid generation package (structured or unstructured). Independence from the flow solver (either inviscid, viscous, aeroelastic) is achieved by obtaining sensitivity information for an advanced gradient‐based optimizer (feasible sequential quadratic programming) by finite‐differences. Results are presented for two‐dimensional aerofoil inverse design and drag optimization problems. Inverse design results demonstrate that a large proportion of the design space is feasible with a relatively low number of design variables using the domain element parameterization. Heavily constrained (in lift, volume, and moment) two‐dimensional aerofoil drag optimization has shown that significant improvements over existing designs can be achieved using this method, through the use of various objective functions. Copyright © 2008 John Wiley & Sons, Ltd.     

The complementary RANS equations for the simulation of viscous flows

A complementary set of Reynolds‐averaged Navier–Stokes (RANS) equations has been developed for steady incompressible, turbulent flows. The method is based on the Helmholtz decomposition of the velocity vector field into a viscous and a potential components. In the complementary RANS solver a potential solution coexists with a viscous solution with the purpose of contributing to a fastest decay of the viscous solution in the far field. The proposed complementary RANS equations have been validated for steady laminar and turbulent flows. The computational results show that the complementary RANS solver is able to produce less grid‐dependent solutions than a conventional RANS solver. Copyright © 2005 John Wiley & Sons, Ltd.     

A high-order solver for simulating vortex-induced vibrations using the sliding-mesh spectral difference method and hybrid grids

We present a high-order solver for simulating vortex-induced vibrations (VIVs) at very challenging situations, for example, VIVs of a row of very closely placed objects with large relative displacements. This solver works on unstructured hybrid grids by employing the high-order tensor-product spectral difference method for quadrilateral grids and the Raviart-Thomas spectral difference method for triangular grids. To deal with the challenging situations where a traditional conforming moving mesh is incapable, we split a computational domain into nonoverlapping subdomains, where each interior subdomain encloses an object and moves freely with respect to its neighbors. A nonuniform sliding-mesh method that ensures high-order accuracy is developed to deal with sliding interfaces between subdomains. A monolithic approach is adopted to seamlessly couple the fluid and solid vibration equations. Moreover, the solver is parallelized to further improve its efficiency on distributed-memory computers. Through a series of numerical tests, we demonstrate that this solver is high-order accurate for both inviscid and viscous flows and has good parallel efficiency, making it ideal for VIV studies.     

A SOLVER USING NEWTON‘S METHOD FOR UNSTEADY VISCOUS FLOWS

A solver is developed for time-accurate computations of viscous flows based on the conception of Newton‘s method. A set of pseudo-time derivatives are added into governing equations and the discretized system is solved using GMRES algorithm. Due to some special properties of GMRES algorithm, the solution procedure for unsteady flows could be regarded as a kind of Newton iteration. The physical-time derivatives of governing equations are discretized using two different approaches, I.e., 3-point Euler backward, and Crank-Nicolson formulas, both with 2nd-order accuracy in time but with different truncation errors. The turbulent eddy viscosity is calculated by using a version of Spalart~Allmaras one-equation model modified by authors for turbulent flows. Two cases of unsteady viscous flow are investigated to validate and assess the solver, I.e., low Reynolds number flow around a row of cylinders and transonic bi-circular-arc airfoil flow featuring the vortex shedding and shock buffeting problems, respectively. Meanwhile, comparisons between the two schemes of timederivative discretizations are carefully made. It is illustrated that the developed unsteady flow solver shows a considerable efficiency and the Crank-Nicolson scheme gives better results compared with Euler method.     

A global simulation method for obtaining reduced reaction mechanisms for use in reactive blast wave flows

A finite rate chemistry solver usually consumes the largest part of the computing time in the numerical simulation of reactive flows. To reduce these costs, a global simulation method has been developed for systematically simplifying detailed reaction mechanisms and a reduced reaction mechanism for CH₄−O₂ is presented. This reduced mechanism accurately replicates the associated detailed mechanism whilst significantly reducing the required computing time. A shock induced methane combustion problem is computed by coupling the reduced reaction mechanism to a 1-D viscous compressible flow solver. As a comparison, a simulation of non-reactive shock flow having the same initial conditions is also performed. These calculations reveal some of the key features found in reactive shock flows. This article was processed by the author using Springer-Verlag TEX PJour2g macro package version 1.1     

A fast and robust fictitious domain method for modelling viscous flows in complex mixers: The example of propellant make‐down

This work deals with the development of a fast three‐dimensional numerical strategy for the simulation of viscous fluid flow in complex mixing systems. The proposed method is based on a distributed Lagrange multiplier fictitious domain method and the use of the low‐cost MINI finite element. Contrary to the previous fictitious domain method developed by our group a few years ago, the underlying partial differential equations are solved here in a coupled manner using a consistent penalty technique. The method is discussed in detail and its precision is assessed by means of experimental data in the case of an agitated vessel. A comparison made with our existing fictitious domain method and its decoupled Uzawa‐based solver clearly shows the advantages of resorting to the MINI finite element and fully coupled solution strategy. The new technique is then applied to the simulation of the flow of a Newtonian viscous fluid in a three‐blade planetary mixer in the context of the production of solid propellants. Copyright © 2008 John Wiley & Sons, Ltd.     

Drag prediction,decomposition and visualization in unstructured mesh CFD solver of TAS‐code

The accuracy of drag prediction in unstructured mesh CFD solver of TAS (Tohoku University Aerodynamic Simulation) code is discussed using a drag decomposition method. The drag decomposition method decomposes total drag into wave, profile, induced and spurious drag components, the latter resulting from numerical diffusion and errors. The mesh resolution analysis is conducted by the drag decomposition method. The effect of an advanced unstructured mesh scheme of U‐MUSCL reconstruction is also investigated by the drag decomposition method. The computational results show that the drag decomposition method reliably predicts drag and is capable of meaningful drag decomposition. The accuracy of drag prediction is increased by eliminating the spurious drag component from the total drag. It is also confirmed that the physical drag components are almost independent of the mesh resolution and scheme modification. Copyright © 2007 John Wiley & Sons, Ltd.     

A finite volume unstructured multigrid method for efficient computation of unsteady incompressible viscous flows

An unstructured non‐nested multigrid method is presented for efficient simulation of unsteady incompressible Navier–Stokes flows. The Navier–Stokes solver is based on the artificial compressibility approach and a higher‐order characteristics‐based finite‐volume scheme on unstructured grids. Unsteady flow is calculated with an implicit dual time stepping scheme. For efficient computation of unsteady viscous flows over complex geometries, an unstructured multigrid method is developed to speed up the convergence rate of the dual time stepping calculation. The multigrid method is used to simulate the steady and unsteady incompressible viscous flows over a circular cylinder for validation and performance evaluation purposes. It is found that the multigrid method with three levels of grids results in a 75% reduction in CPU time for the steady flow calculation and 55% reduction for the unsteady flow calculation, compared with its single grid counterparts. The results obtained are compared with numerical solutions obtained by other researchers as well as experimental measurements wherever available and good agreements are obtained. Copyright © 2004 John Wiley & Sons, Ltd.     

用鲁棒Riemann求解器和运动重叠网格计算旋翼粘性绕流

发展了一种基于鲁棒Riemann求解器和运动重叠网格技术计算直升机悬停旋翼流场的方法。基于惯性坐标系,悬停旋翼流场是非定常流场,控制方程为可压缩Reynolds平均Navier-Stoke方程,其对流项采用Roe近似Reimann求解器离散,使用改进的五阶加权基本无振荡格式进行高阶重构,非定常时间推进采用含牛顿型LUSGS子迭代的全隐式双时间步方法。为实施旋转运动和便于捕捉尾迹,计算采用运动重叠网格技术。计算得到的桨叶表面压力分布及桨尖涡涡核位置都与实验结果吻合较好。数值结果表明:所发展方法对桨尖涡具有较高的分辨率,对激波具有较好的捕捉能力,该方法可进一步推广到前飞旋翼粘性绕流的计算。     

Drag characteristics of longitudinal and transverse riblets at low dimensionless spacings

A surface grooved with microscopic riblets aligned parallel to the flow is an effective means to reduce the turbulent skin friction up to 10% compared to a smooth surface. The maximum drag reduction is found for a dimensionless rib spacing s ⁺ in the range of 15–17. For s ⁺ < 10, a linear behaviour of the drag reduction curve is predicted by viscous theory. This linear slope of the drag reduction curve is in contradiction to Schlichting’s postulation of a hydraulically smooth behaviour of small-scale roughness in a turbulent flow. This regime of evanescent dimensionless rib spacings is investigated experimentally by direct wall shear stress measurements in a fully developed channel flow. Additionally, a numerical calculation of the viscous flow over riblets was carried out to predict the drag reducing behaviour. The experimental results show a linear drag reducing behaviour down to s ⁺ = 0.3, which is in good agreement with the numerical results of the viscous simulation. The postulation of Schlichting’s hydraulically smooth regime of a rough surface was not confirmed, neither for a riblet surface nor for a surface geometry with grooves oriented perpendicular to the flow. In the latter case, the drag increases as a quadratic function of the roughness height.