低Mach数翼型绕流数值模拟的低耗散预处理格式

相倩; 吴颂平; 李椿萱; 曹宁

doi:10.3879/j.issn.1000-0887.2011.05.008

低Mach数翼型绕流数值模拟的低耗散预处理格式

doi: 10.3879/j.issn.1000-0887.2011.05.008

相倩^1,2,3,
吴颂平^1,2,3,
李椿萱^1,2,3,
曹宁^1,2,3

1.
北京航空航天大学航空科学与工程学院, 北京 100191;2.北京航空航天大学国家计算流体力学实验室, 北京 100191;3.北京航空航天大学流体力学教育部重点实验室, 北京100191

基金项目: 973国家基础研究基金资助项目(2007CB714600)

详细信息

作者简介:
相倩(1984- ),女,河北石家庄人,博士生(联系人.E-mail:axg220377@gmail.com).

中图分类号: V211.3
计量
- 文章访问数: 1828
- HTML全文浏览量: 204
- PDF下载量: 840
- 被引次数: 0
出版历程
- 收稿日期: 2011-01-25
- 修回日期: 2011-02-21
- 刊出日期: 2011-05-15

Low-Diffusion Preconditioning Scheme for Numerical Simulation of Low-Speed Flows Past Airfoil

XIANG Qian^1,2,3,
WU Song-ping^1,2,3,
LEE Chun-xuan^1,2,3,
CAO Ning^1,2,3

1.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, P. R. China;

摘要

摘要: 低Mach数流动中，基于可压缩流动的数值模拟算法存在严重的刚性问题，预处理方法可以有效地解决这一问题，但其计算结果不稳定．基于原有的预处理Roe格式，引入可调节参数，得到一种新的低耗散格式．该格式可以减弱边界层以及极低速区域的过度耗散，使得整个流场计算稳定．低Mach数、低Reynolds数定常圆柱绕流和低Mach数、高Reynolds数翼型(NACA0012和S809)绕流3个验证算例表明,带可调节参数的低耗散预处理方法正确可靠,是低速流动数值模拟的有效方法．
- 数值模拟 /
- 预处理 /
- 定常流 /
- 翼型
Abstract: The reconditioning technique addresses the stiffness of low Mach number flow, while the stability was poor. Based on the conventional preconditioning method of Roe's scheme, a new low-diffusion scheme was proposed. An adjustable parameter was introduced to control the numerical dis-sipation in the new scheme, especially the over dissipation in the boundary layer and extremely low speed region. Numerical simulations of low Mach and low Reynolds number flows over a cylinder, low Mach and high Reynolds number flows over NACA0012 and NH02-18 airfoils were performed to validate the new scheme. All results of the three test cases are found to agree well with experiment data, demonstrating the applicability of the suggested scheme to low Mach number flow simulations.
- numerical simulation /
- preconditioning /
- steady flow /
- airfoil

HTML全文

参考文献(10)

[1]	Hansen M O L. Aerodynamics of Wind Turbines[M]. London, Sterling, VA:Earthscan, 2008.
[2]	Turkel E. Preconditioned methods for solving the incompressible and low speed compressible equations [J]. Journal of Computational Physics, 1987, 72(2): 277-298. doi: 10.1016/0021-9991(87)90084-2
[3]	Merkle C L, Sullivan J Y, Buelow P E O, Venkateswaran S. Computation of flows with arbitrary equations of state[J]. AIAA Journal, 1998, 36(4): 515-521. doi: 10.2514/2.424
[4]	Choi D, Merkle C L. Application of time-iterative schemes to incompressible flow[J]. AIAA Journal, 1985, 28(10): 1518-1524.
[5]	黄典贵. 基于Roe格式的可压与不可压流的统一计算方法[J].应用数学和力学, 2006, 27(6): 669-674. (HUANG Dian-gui. Unified computation of flow with compressible and incompressible fluid based on Roe’s scheme[J].Applied Mathematics and Mechanics(English Edition), 2006, 27(6) :757-763.)
[6]	Venkateswaran S, Li D, Merkle C L. Influence of stagnation regions on preconditioned solutions at low speeds[C]41st Aerospace Sciences Meeting & Exhibit, Reno, NV; United States; 6-9 Jan 2003: 2003-2435.
[7]	李雪松, 徐建中, 顾春伟. 预处理方法与大涡模拟工程应用[J]. 中国科学, G辑, 2009, 39(1): 83-90. (LI Xue-song, XU Jian-zhong, GU Chun-wei. Preconditioning method on the application of LES[J]. Sci China, Ser G-Phys Mech Astron, 2009, 39(1): 83-90.(in Chinese))
[8]	Fornberg B. A numerical study of steady viscous flow past a circular cylinder[J]. J Fluid Mech, 1980, 98: 819-855. doi: 10.1017/S0022112080000419
[9]	Ladson Charles L. Effects of independent variation of Mach and reynolds numbers on the low-speed aerodynamic characteristics of the NACA0012 airfoil section[R]. Washington, District of Columbia. National Aeronautics and Space Administration. TM-4074, 1988.
[10]	Ramsay R, Hoffmann M J, Gregorek G M. Effects of grit roughness and pitch oscillations on the S809 airfoil[R]. Report Number(s) NREL / TP-442-7817. National Renewable Energy Lab, Golden, CO (United States), 1995. doi: 10.2172/205563.