高超声速化学非平衡流动Navier-Stokes/DSMC耦合算法

doi:10.7527/S1000-6893.2018.22229

流体力学与飞行力学

本期目录 | 过刊浏览 | 高级检索

前一篇 | 后一篇

高超声速化学非平衡流动Navier-Stokes/DSMC耦合算法

李中华¹, 党雷宁¹, 李志辉^1,2

1. 中国空气动力研究与发展中心超高速空气动力研究所, 绵阳 621000;
2. 国家计算流体力学实验室, 北京 100083

收稿日期:2018-04-20 修回日期:2018-06-11 出版日期:2018-10-15 发布日期:2018-06-25
通讯作者: 李中华 E-mail:lzhzcb@aliyun.com
基金资助:
国家“973”计划（2014CB744100）；国家自然科学基金（91530319，11325212）

Navier-Stokes/DSMC hybrid algorithm for hypersonic flows with chemical non-equilibrium

LI Zhonghua¹, DANG Leining¹, LI Zhihui^1,2

1. Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China;
2. National Laboratory of Computational Fluid Dynamics, Beijing 100083, China

Received:2018-04-20 Revised:2018-06-11 Online:2018-10-15 Published:2018-06-25
Supported by:
National Basic Research Program of China (2014CB744100); National Natural Science Foundation of China (91530319, 11325212)

摘要/Abstract

摘要： 基于相同的化学反应模型，在已有计算流体力学（CFD）和直接仿真蒙特卡罗（DSMC）方法及程序的基础上，采用Modular Particle-Continuum（MPC）耦合技术，建立了包含化学非平衡Navier-Stokes/DSMC耦合算法。算法结构中DSMC计算区域在CFD计算结果上根据当地克努森数自动选取。发展了适用于流场分区信息交换的亚松弛技术，抑制DSMC方法对CFD计算的影响。把DSMC方法和CFD的应用范围拓展到过渡流区，为复杂飞行器近连续过渡流区高超声速化学非平衡流动数值模拟研究提供了一种工程适用的预测分析手段。通过对二维圆柱高超声速化学非平衡绕流的算例与其他结果的比较研究，表明耦合算法不论在流场结构、流场非平衡现象，还是飞行器表面参数、整体气动力/热特性方面，都能够得到与全DSMC计算吻合的结果，证实了所建立的Navier-Stokes/DSMC耦合计算模型与方法的有效性和可靠性。仿真了某航天器解体碎片在过渡区的化学非平衡流动，得到碎片在过渡区的气动力/热特性，为碎片的陨落计算提供依据。

关键词: 过渡流, CFD, DSMC, 信息交换, 耦合算法, 化学非平衡

Abstract: Based on the same chemical reaction model, an Navier-Stokes/Direct Simulation Monte Carlo (DSMC) hybrid algorithm with chemical non-equilibrium is proposed by using the Modular Particle-Continuum (MPC) technique using current Computational Fluid Dynamics (CFD) and DSMC methods. The DSMC region is selected automatically according to the CFD results in this hybrid scheme based on local Knudson numbers. A sub-relax technique for information exchange between CFD and DSMC is developed to restrain the effect of statistical fluctuation from DSMC to CFD. This extends the application of the DSMC and the CFD method, and provides an approach to predict the chemical non-equilibrium characteristics in the near-continuum transition flow regime. The hypersonic flow with chemical non-equilibrium around a 2D cylinder is simulated by the Navier-Stokes/DSMC hybrid method proposed. A comparison of the simulation result obtained with the method proposed and that with other methods shows that the results obtained with the method proposed are good agreement with the results obtained with full DSMC in terms of flow structure, non-equilibrium phenomenon, surface parameters and aerodynamics characteristics. This verifies the adaptability and reliability of the proposed Navier-Stokes/DSMC hybrid algorithm in simulating hypersonic flows for the transition flow regime. The chemical non-equilibrium flows around a fragment from a disintegrated aerocraft are simulated to obtain the aerodynamic force and thermal characteristics of the fragment in the transition region, thus providing some reference for simulation of fragment fall.

Key words: transition flow, CFD, DSMC, information exchange, hybrid algorithm, chemical non-equilibrium

中图分类号:

V411
O356

李中华, 党雷宁, 李志辉. 高超声速化学非平衡流动Navier-Stokes/DSMC耦合算法[J]. 航空学报, 2018, 39(10): 122229-122229.

LI Zhonghua, DANG Leining, LI Zhihui. Navier-Stokes/DSMC hybrid algorithm for hypersonic flows with chemical non-equilibrium[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(10): 122229-122229.

参考文献

[1] SCHWANEKAMP T, BÜTÜNLEY J, SIPPEL M. Preliminary multidisciplinary design studies on an upgraded 100 passenger SpaceLiner derivative:AIAA-2012-5808[R]. Reston, VA:AIAA, 2012.
[2] SIPPEL M, SCHWANEKAMP T, BAUSER C. Technical maturation of the SpaceLiner concept:AIAA-2012-5850[R]. Reston, VA:AIAA, 2012.
[3] HOLDEN M S, WADHAMS T P, MACLEAN M, et al. Experimental studies in LENS I and X to evaluate real gas effects on hypervelocity vehicle performance:AIAA-2007-0204[R]. Reston, VA:AIAA, 2007.
[4] PRABHU D K, PAPADOPOULOS P E, DAVIES C B, et al. Shuttle orbiter contingency abort aerodynamics Ⅱ:Real-gas effects and high angles of attack:AIAA-2003-1248[R]. Reston, VA:AIAA, 2003.
[5] HANNAN B. Thermo-chemical nonequilibrium effects on the aerothermodynamics of hypersonic vehicles[D]. Raleigh, NC:North Carolina State University, 1993:37-56.
[6] BONNIE J M, MICHAEL J Z, SANFORD G. NASA Glenn coefficients for calculating thermodynamic properties of individual species:NASA/TP-2002-211556[R].Washington, D.C.:NASA, 2002.
[7] BLOTTNER F G, JOHNSON M, ELLIS M. Chemically reacting viscous flow program for multi-component gas mixtures:SC-RR-70-754[R]. Albuquerque, NM:Sandia National Laboratories, 1971.
[8] ANDERSON J D. Hypersonic and high-temperature gas dynamics[M]. Reston, VA:AIAA, 2006:575-597.
[9] WRIGHT M J, CANDLER G V, PRAMPOLINI M. Data-parallel lower-upper relaxation method for the Navier-Stokes equations[J]. AIAA Journal, 1996, 34(7):1371-1377.
[10] 张涵信, 陈坚强, 高树椿. H₂/O₂燃烧的超声速非平衡流动的数值模拟[J]. 宇航学报, 1994, 15(2):14-23. ZHANG H X, CHEN J Q, GAO S C. Numerical simulation of supersonic nonequilibrium flows for H₂/O₂ combustions[J]. Journal of Astronautics, 1994, 15(2):14-23(in Chinese).
[11] 刘君. 非平衡流计算方法及其模拟激波诱导振荡燃烧[J]. 空气动力学学报, 2003, 21(1):53-58. LIU J. A new nonequilibrium numerical method and simulation of oscillating shock-induced combustion[J]. Acta Aerodynamica Sinica, 2003, 21(1):53-58(in Chinese).
[12] 李海燕. 高超声速高温气体流场的数值模拟[D].绵阳:中国空气动力研究与发展中心, 2007:63-64. LI H Y. Numerical simulation of hypersonic high temperature flowfield[D]. Mianyang:China Aerodynamics Research and Development Center, 2007:63-64(in Chinese).
[13] BIRD G A. Molecular gas dynamics and the direct simulation of gas flows[M]. London:Oxford Univisity Press, 1994:123-146.
[14] WEN C Y, CHEN Y S, LIANG S M, et al. Numerical simulations of nonequilibrium flows over rounded models at reentry speeds:AIAA-2012-5906[R]. Reston, VA:AIAA, 2012.
[15] BIRD G A. Approach to transitional equilibrium in a rigid sphere gas[J]. Physics of Fluids, 1963, 6(10):1518-1519.
[16] ALEXANDER F J, GARCIA A L. The direct simulation Monte Carlo method[J]. Computers in Physics, 1997, 11(6):588-593.
[17] BONDAR Y A, SHEVYRIN A A. DSMC modeling of high-temperature chemical reactions in air:AIAA-2011-3128[R]. Reston, VA:AIAA, 2011.
[18] 沈青. 稀薄气体动力学[M]. 北京:国防工业出版社, 2003:228-275. SHEN Q. Rarefied gas dynamics[M]. Beijing:National Defence Industry Press, 2003:228-275(in Chinese).
[19] 陈伟芳, 吴明巧, 任兵. DSMC/EPSM混合算法研究[J]. 计算力学学报, 2003, 20(3):274-278. CHEN W F, WU M Q, REN B. On study of hybrid DSMC/EPSM method[J]. Chinese Journal of Computational Mechanics, 2003, 20(3):274-278(in Chinese).
[20] 方明. 极高速再入条件下稀薄气体电离热化学非平衡绕流DSMC方法与应用研究[D]. 北京:北京航空航天大学, 2016:30-41. FANG M. Study on DSMC method and application of thermal-chemical ionized non-equilibrium flows during hypervelocity reentry[D]. Beijing:Beihang University, 2016:30-41(in Chinese).
[21] KOPPENWALLNER G, LEGGE H. Drag of bodies in rarefied hypersonic flow:AIAA-1985-0998[R]. Reston, VA:AIAA, 1985.
[22] BOYD I D. Predicting the breakdown of the continuum equations under rarefied flow conditions[C]//Proceedings of the 23th International Symposium on Rarefied Gas Dynamics. College Park, MD:American Institute of Physics, 2003:899-906.
[23] LI Z H, ZHANG H X. Study on gas kinetic unified algorithm for flows from rarefied transition to continuum[J]. Journal of Computational Physics, 2004, 193(2):708-738.
[24] LI Z H, FANG M, WU J L, et al. Convergence proof of the DSMC method and the gas-kinetic unified algorithm for the Boltzmann equation[J]. Science China Physics, Mechanics & Astronomy, 2013, 56(2):404-417.
[25] LI Z H, ZHANG H X, FU S, et al. A gas kinetic algorithm for flows in microchannel[J]. International Journal of Nonlinear Sciences and Numerical Simulation, 2005, 6(3):261-270.
[26] WU J L, LI Z H, PENG A P, et al. Numerical simulations of unsteady flows from rarefied transition to continuum using gas-kinetic unified algorithm[J]. Advances in Applied Mathematics and Mechanics, 2015, 7(5):569-596.
[27] WU J L, LI Z H, PENG A P, et al. Numerical study on rarefied unsteady jet flow expanding into vacuum using gas-kinetic unified algorithm[J]. Computers and Fluids, 2017, 155:50-61.
[28] WADSWORTH D C, ERWIN D A. Two-dimensional hybrid continuum/particle approach for rarefied flows:AIAA-1992-2975[R]. Reston, VA:AIAA, 1992.
[29] HASH D B, HASSAN H A. A hybrid DSMC/Navier-Stokes solver:AIAA-1995-0410[R]. Reston, VA:AIAA, 1995.
[30] SCHWARTZENTRUBER T E, SCALABRIN L C, BOYD I D. Modular implementation of a hybrid DSMC-NS algorithm for hypersonic non-equilibrium flows:AIAA-2007-0613[R]. Reston, VA:AIAA, 2007.
[31] SCHWARTZENTRUBER T E, SCALABRIN L C, BOYD I D. Hybrid particle-continuum simulations of low Knudsen number hypersonic flows:AIAA-2007-3892[R]. Reston, VA:AIAA, 2007.
[32] BURT J M, BOYD I D. A multiscale particle approach for continuum/rarefied flow simulation:AIAA-2008-1184[R]. Reston, VA:AIAA, 2008.
[33] CARLSON H A, BOYD I D, CANDLER G. A hybrid CFD-DSMC method of modeling continuum-rarefied flows:AIAA-2004-1180[R]. Reston, VA:AIAA, 2004.
[34] BURT J M, BOYD I D. A hybrid particle approach for continuum and rarefied flow simulation[J]. Journal of Computational Physics, 2009, 228(2):460-475.
[35] LI Z H, LI Z H, LI H Y, et al. Application of hybrid N-S/DSMC method in hypersonic transitional flow[C]//Proceedings of the 28th International Symposium on Rarefied Gas Dynamics. College Park, MD:American Institute of Physics, 2012:435-442.
[36] LI Z H, LI Z H, LI H Y, et al. N-S/DSMC hybrid simulation of hypersonic flow over blunt body including wakes[C]//Proceedings of the 29th International Symposium on Rarefied Gas Dynamics. College Park, MD:American Institute of Physics, 2014:519-526.
[37] 李中华, 李志辉, 李海燕, 等. 过渡流区NS/DSMC耦合算法研究[J]. 空气动力学学报, 2013, 31(3):282-287. LI Z H, LI Z H, LI H Y, et al. Research of CFD/DSMC hybrid numerical method in rarefied flow[J]. Acta Aerodynamica Sinica, 2013, 31(3):282-287(in Chinese).
[38] WANG W L. A hybrid particle/continuum Approach for nonequilibrium hypersonic flows[D]. Ann Arbor, MI:University of Michigan, 2004:96-106.
[39] DESCHENES T R, BOYD I D. Extension of a modular particle-continuum method to vibrationally excited, hypersonic flows[J]. AIAA Journal, 2011, 49(9):1951-1959.
[40] DESCHENES T R, BOYD I D, SCHWARTZENTRUBER T E. Incorporating vibrational excitation in a hybrid particle-continuum method:AIAA-2008-4106[R]. Reston, VA:AIAA, 2008.
[41] GARCIA A L, ALDER B J. Generation of the Chapman-Enskog distribution[J]. Journal of Computational Physics, 1998, 140(1):66-77.

E-mail：hkxb@buaa.edu.cn

关于我们

期刊社服务

专业学科

封面文章

友情链接

主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

高超声速化学非平衡流动Navier-Stokes/DSMC耦合算法

Navier-Stokes/DSMC hybrid algorithm for hypersonic flows with chemical non-equilibrium

PDF (PC)

可视化

摘要/Abstract

引用本文

使用本文

参考文献

相关文章 15

编辑推荐

Metrics

本文评价

[1]	夏侯唐凡, 陈江涛, 邵志栋, 吴晓军, 刘宇. 随机和认知不确定性框架下的CFD模型确认度量综述[J]. 航空学报, 2022, 43(8): 25716-025716.
[2]	陈广强, 豆国辉, 魏昊功, 邹昕, 李齐, 刘周, 周伟江. 火星探测器大气数据测量方法[J]. 航空学报, 2022, 43(3): 626619-626619.
[3]	王海峰, 邓枫, 刘学强, 覃宁. 基于喷流作用的自然层流翼型阵风载荷减缓控制[J]. 航空学报, 2022, 43(11): 526767-526767.
[4]	阎超. 航空CFD四十年的成就与困境[J]. 航空学报, 2022, 43(10): 526490-526490.
[5]	刘朋欣, 袁先旭, 孙东, 傅亚陆, 李辰. 高温化学非平衡湍流边界层直接数值模拟[J]. 航空学报, 2022, 43(1): 124877-124877.
[6]	刘朋欣, 袁先旭, 梁飞, 李辰, 孙东. 高温化学非平衡湍流边界层脉动量象限分析[J]. 航空学报, 2021, 42(S1): 726338-726338.
[7]	李鹏, 陈坚强, 丁明松, 梅杰, 何先耀, 董维中. LENS风洞试验返回器模型气动热特性模拟[J]. 航空学报, 2021, 42(S1): 726400-726400.
[8]	吴忧, 徐旭, 陈兵, 杨庆春. 高马赫数下横/逆向喷流干扰流场数值研究[J]. 航空学报, 2021, 42(S1): 726359-726359.
[9]	李鹏, 陈坚强, 丁明松, 何先耀, 赵钟, 董维中. NNW-HyFLOW高超声速流动模拟软件框架设计[J]. 航空学报, 2021, 42(9): 625718-625718.
[10]	袁先旭, 陈坚强, 杜雁霞, 郭启龙, 肖光明, 傅亚陆, 梁飞, 涂国华. 国家数值风洞(NNW)工程中的CFD基础科学问题研究进展[J]. 航空学报, 2021, 42(9): 625733-625733.
[11]	陈坚强, 吴晓军, 张健, 李彬, 贾洪印, 周乃春. FlowStar:国家数值风洞(NNW)工程非结构通用CFD软件[J]. 航空学报, 2021, 42(9): 625739-625739.
[12]	李左飙, 温风波, 唐晓雷, 苏良俊, 王松涛. 基于深度学习的单排孔气膜冷却性能预测[J]. 航空学报, 2021, 42(4): 524331-524331.
[13]	靳旭红, 黄飞, 程晓丽, 苏鹏辉. Maxwell气固相互作用模型对稀薄高超声速凹腔绕流流动特征和热环境的影响[J]. 航空学报, 2021, 42(3): 124118-124118.
[14]	李锦, 耿湘人, 陈坚强, 江定武, 李红喆. DSMC量子动理学模型在火星再入流动中的应用[J]. 航空学报, 2020, 41(7): 123240-123240.
[15]	周铸, 余永刚, 刘刚, 陈作斌, 何开锋. 飞翼布局组合舵面航向控制特性综合研究[J]. 航空学报, 2020, 41(6): 523422-523422.