DDES延迟函数在超声速底部流动中的性能分析

杜若凡; 阎超; 韩政; 向星皓; 屈峰

doi:10.13700/j.bh.1001-5965.2016.0602

DDES延迟函数在超声速底部流动中的性能分析

doi: 10.13700/j.bh.1001-5965.2016.0602

杜若凡^{1, 2},
阎超^1, ,,
韩政¹,
向星皓³,
屈峰²

1.
北京航空航天大学航空科学与工程学院, 北京 100083
2.
中国空间技术研究院载人航天总体部, 北京 100094
3.
中国空气动力研究与发展中心, 绵阳 621000

基金项目:

国家自然科学基金 11402016

详细信息

作者简介:
杜若凡男, 博士研究生。主要研究方向:计算流体力学、湍流模型

阎超男, 博士, 教授, 博士生导师。主要研究方向:计算流体力学、空气动力学

通讯作者:
阎超, E-mail:yanchao@buaa.edu.cn

中图分类号: V221.3
计量
- 文章访问数: 713
- HTML全文浏览量: 59
- PDF下载量: 415
- 被引次数: 0
出版历程
- 收稿日期: 2016-07-15
- 录用日期: 2016-08-11
- 网络出版日期: 2017-08-20

Performance of delayed functions in DDES for supersonic base flow

DU Ruofan^{1, 2},
YAN Chao^{1
, ,},
HAN Zheng¹,
XIANG Xinghao³,
QU Feng²

1.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
Institute of Manned Space System Engineering, China Academy of Space Technology, Beijing 100094, China
3.
China Aerodynamics Research and Development Center, Mianyang 621000, China

Funds:

National Natural Science Foundation of China 11402016

More Information

Corresponding author: YAN Chao, E-mail:yanchao@buaa.edu.cn

摘要

摘要:
DDES是广泛应用的一类RANS/LES混合方法，其通过引入延迟函数保证近壁区的RANS模化，对分离流动十分有效。目前DDES已发展了多种不同的延迟函数，但对各延迟函数的性能特点认识尚不够充分，尤其缺乏超声速流动中的相关研究。围绕DDES方法中不同延迟函数开展研究工作，选取超声速底部流动作为测试算例，通过与实验数据的系统对比分析，考察不同延迟函数在超声速分离流动中的分布规律、作用效果及模型求解能力。研究表明，不同延迟函数作用范围与求解能力存在差异，其中DDES-F₁能够在起到保护作用的同时不损害模型的求解精度，对该流动较为有效，所得结果与实验数据吻合较好。
- DDES /
- 超声速底部流动 /
- 延迟函数 /
- 湍流 /
- 计算流体力学
Abstract:
The DDES is a widely used approach among RANS/LES hybrid methods. It introduces the delayed function to ensure full RANS mode in the near-wall region, and has been proven to be quite efficient for separated flows. Up to date, various different delayed functions have been developed. However, the understanding to the performance and characteristics of different delayed functions still remains not comprehensive, especially lacking investigation on supersonic flows. The research focuses on the different delayed functions in the DDES methods by employing the supersonic base flow as the validation case. Through systematic comparisons with the experimental data and detailed analyses, the distributions and shielding behavior of different delayed functions together with resolving capabilities of different models are investigated. Studies show that there exist discrepancies in the shielding behavior and resolving capabilities between different delayed functions. Besides, DDES-F₁ behaves appropriately in this supersonic separated flow and reproduces the experimental data very well, providing sufficient protection without impairing the model's numerical accuracy.
- DDES /
- supersonic base flow /
- delayed functions /
- turbulence /
- computational fluid dynamics

HTML全文

图 1 底部流动外形和计算网格示意图

Figure 1. Schematic diagram of configuration and computational grid for base flow

下载: 全尺寸图片幻灯片

图 2 对称面时均流场马赫数云图

Figure 2. Mach number contours of time-averaged flow field in symmetry plane

下载: 全尺寸图片幻灯片

图 3 不同延迟函数分布与RANS、LES区域划分云图

Figure 3. Contours of distribution of different delayed functions and placement of RANS and LES regions

下载: 全尺寸图片幻灯片

图 4 对称面瞬时流场涡量云图

Figure 4. Vorticity contours of instantaneous flow field in symmetry plane

下载: 全尺寸图片幻灯片

图 5 功率谱密度分布

Figure 5. Distribution of power spectral density

下载: 全尺寸图片幻灯片

图 6 时均底部压力系数分布

Figure 6. Distribution of time-averaged base pressure coefficient

下载: 全尺寸图片幻灯片

图 7 尾迹中心线时均流向速度分布

Figure 7. Distribution of time-averaged centerline streamwise velocity in wake

下载: 全尺寸图片幻灯片

图 8 不同站位的时均流向速度分布

Figure 8. Distribution of time-averaged streamwise velocity at different locations

下载: 全尺寸图片幻灯片

图 9 不同站位的雷诺剪切应力分布

Figure 9. Distribution of Reynolds shear stresses at different locations

下载: 全尺寸图片幻灯片

参考文献(17)

[1]	阎超, 于剑, 徐晶磊, 等.CFD模拟方法的发展成就与展望[J].力学进展, 2011, 41(5):562-589. doi: 10.6052/1000-0992-2011-5-lxjzJ2010-082 YAN C, YU J, XU J L, et al.On the achievements and prospects for the methods of computational fluid dynamics[J].Advances in Mechanics, 2011, 41(5):562-589(in Chinese). doi: 10.6052/1000-0992-2011-5-lxjzJ2010-082
[2]	SLOTNICK J, KHODADOUST A, ALONSO J, et al. CFD vision 2030 study:A path to revolutionary computational aerosciences:NASA/CR-2014-218178[R].Hanover:NASA Center for Aerospace Information, 2014.
[3]	FRÖHLICH J, VON TERZI D. Hybrid LES/RANS methods for the simulation of turbulent flows[J].Progress in Aerospace Sciences, 2008, 44(5):349-377. doi: 10.1016/j.paerosci.2008.05.001
[4]	SPALART P R, JOU W H, STRELETS M, et al. Comments on the feasibility of LES for wings and on a hybrid RANS/LES approach[C]//Proceedings of 1st AFOSR International Conference on DNS/LES, Advances in DNS/LES. Columbus:Greyden Press, 1997:137-147.
[5]	STRELETS M. Detached eddy simulation of massively separated flows:AIAA-2001-0879[R].Reston:AIAA, 2001.
[6]	SPALART P R. Detached-eddy simulation[J]. Annual Review of Fluid Mechanics, 2009, 41:181-202. doi: 10.1146/annurev.fluid.010908.165130
[7]	MENTER F R, KUNTZ M, LANGTRY R. Ten years of industrial experience with the SST turbulence model[C]//Turbulence, Heat and Mass Transfer 4. Redding:Begell House, Inc., 2003:625-632.
[8]	SPALART P R, DECK S, SHUR M L, et al. A new version of detached-eddy simulation, resistant to ambiguous grid densities[J].Theoretical and Computational Fluid Dynamics, 2006, 20:181-195. doi: 10.1007/s00162-006-0015-0
[9]	HERRIN J L, DUTTON J C. Supersonic base flow experiments in the near wake of a cylindrical afterbody[J]. AIAA Journal, 1994, 32(1):77-83. doi: 10.2514/3.11953
[10]	BOURDON C J, DUTTON J C. Planar visualizations of large-scale turbulent structures in axisymmetric supersonic separated flows[J]. Physics of Fluids, 1999, 11(1):201-213. doi: 10.1063/1.869913
[11]	TUCKER P K, SHYY W. A numerical analysis of supersonic flow over an axisymmetric afterbody:AIAA-1993-2347[R]. Reston:AIAA, 1993.
[12]	FUREBY C, NILSSON Y, ANDERSSON K. Large eddy simulation of supersonic base flow:AIAA-1999-0426[R].Reston:AIAA, 1999.
[13]	PENG S H.Algebraic hybrid RANS/LES modelling applied to incompressible and compressible turbulent flows:AIAA-2006-3910[R].Reston:AIAA, 2006.
[14]	高瑞泽, 阎超.LES/RANS混合方法对超声速底部流动的应用[J].北京航空航天大学学报, 2011, 37(9):1095-1099. http://bhxb.buaa.edu.cn/CN/abstract/abstract12068.shtml GAO R Z, YAN C. LES/RANS hybrid method for supersonic axisymmetric base flow[J].Journal of Beijing University of Aeronautics and Astronautics, 2011, 37(9):1095-1099(in Chinese). http://bhxb.buaa.edu.cn/CN/abstract/abstract12068.shtml
[15]	LUO D H, YAN C, WANG X Y. Computational study of supersonic turbulent-separated flows using partially averaged Navier-Stokes method[J].Acta Astronautica, 2015, 107:234-246. doi: 10.1016/j.actaastro.2014.11.029
[16]	SIMON F, DECK S, GUILLEN P, et al. Reynolds-averaged Nacier-Stokes/large-eddy simulations of supersonic base flow[J]. AIAA Journal, 2006, 44(11):2578-2590. doi: 10.2514/1.21366
[17]	郑玮琳, 阎超.XY-SAS模型中不同网格尺度限制器的影响分析[J].北京航空航天大学学报, 2014, 40(12):1725-1729. http://bhxb.buaa.edu.cn/CN/abstract/abstract13104.shtml ZHENG W L, YAN C. Influence analysis on grid scale limiter of XY-SAS model[J].Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(12):1725-1729(in Chinese). http://bhxb.buaa.edu.cn/CN/abstract/abstract13104.shtml