热化学非平衡流动自适应松弛耦合模拟方法

doi:10.7527/S1000-6893.2025.33061

Abstract

Abstract:

The efficiency of numerical simulation for thermochemical non-equilibrium flow of hypersonic vehicles has always been one of the pain points in engineering applications. Based on the time-consuming analysis of thermochemical non-equilibrium flow simulation， an adaptive relaxation coupling simulation method of thermochemical non-equilibrium flow was established by capturing and judging the flow field characteristics or iterative characteristics. The accuracy and efficiency of the adaptive relaxation coupling simulation method were tested and analyzed under different parameters， different physical and chemical models， as well as different thermochemical non-equilibrium flow characteristics. The results show that， the calculation time-consuming ratio of non-equilibrium source term and its Jacobian matrices processing， multi-component gas energy function and transport coefficient could reach 62.04% under the current conditions. The adaptive relaxation coupling simulation method established based on time-consumption analysis can significantly enhance computational efficiency， reducing computational time by up to 45.70%. The proposed method does not reduce the convergence and accuracy of numerical iteration， and has the same calculation fidelity and accuracy as the coupling simulation method of full physical models. It can be easily implemented on various static or dynamic software architectures without changing the computational domain dynamically and adjusting the logical structure or computational flow greatly. This method is more effective in fine physical and chemical model， and can partly solve the difficulty of balancing computational accuracy and efficiency of complex engineering problems.

Key words: hypersonic flow, high temperature gas effect, thermochemical non-equilibrium, adaptive relaxation coupling, hypersonic vehicles

CLC Number:

V411.3

Mingsong DING, Qingzong LIU, Tao JIANG, Peng LI, Jie MEI, Aoxiao FU-YANG. Adaptive relaxation coupling simulation method for thermochemical non-equilibrium flow[J]. Acta Aeronautica et Astronautica Sinica, 2026, 47(19): 133061.

Figures/Tables 15

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References 35

[1]	BOYD I D. Modeling of associative ionization reactions in hypersonic rarefied flows［J］. Physics of Fluids， 2007， 19（9）： 096102.
[2]	OZAWA T， LEVIN D A， NOMPELIS I， et al. Particle and continuum method comparison of a high-altitude， extreme-Mach-number reentry flow［J］. Journal of Thermophysics and Heat Transfer， 2010， 24（2）： 225-240.
[3]	莫凡，高振勋，蒋崇文，等. 高温化学非平衡效应对高超声速飞行器气动力/热影响的数值研究进展［J］. 中国科学：物理学力学天文学， 2021， 51（10）： 104703.
	MO F， GAO Z X， JIANG C W， et al. Progress in the numerical study on the aerodynamic and thermal characteristics of hypersonic vehicles： High-temperature chemical non-equilibrium effect［J］. Scientia Sinica （Physica， Mechanica & Astronomica）， 2021， 51（10）： 104703 （in Chinese）.
[4]	WEN C Y， MASSIMI H S， CHEN Y S， et al. Numerical simulations of nonequilibrium flows over rounded models at reentry speeds： AIAA-2012-5906［R］. Reston： AIAA， 2012.
[5]	王京盈. 高速高温流动的化学非平衡及热辐射耦合效应研究［D］. 北京：北京航空航天大学， 2015： 1-165.
	WANG J Y. Numerical study on coupled effects of the chemical nonequilibrium and thermal radiation in high speed and high temperature flows［D］. Beijing： Beihang University， 2015： 1-165 （in Chinese）.
[6]	董维中，高铁锁，丁明松，等. 高超声速飞行器表面温度分布与气动热耦合数值研究［J］. 航空学报， 2015， 36（1）： 311-324.
	DONG W Z， GAO T S， DING M S， et al. Numerical study of coupled surface temperature distribution and aerodynamic heat for hypersonic vehicles［J］. Acta Aeronautica et Astronautica Sinica， 2015， 36（1）： 311-324 （in Chinese）.
[7]	赵钟. 复杂外形高雷诺数数值模拟的混合网格生成与多重网格法研究［D］. 绵阳：中国空气动力研究与发展中心， 2011.
	ZHAO Z. Hybrid grid generation technique and multigrid method for viscous flow simulation of complex geometries［D］. Mianyang： China Aerodynamics Research and Development Center， 2011 （in Chinese）.
[8]	LI P， CHEN J Q， DING M S， et al. A multi-stage coupling adaptive method for thermochemical nonequilibrium gas［J］. Computers & Fluids， 2023， 261： 105916.
[9]	唐志共，张益荣，陈坚强，等. 更准确、更精确、更高效：高超声速流动数值模拟研究进展［J］. 航空学报， 2015， 36（1）： 120-134.
	TANG Z G， ZHANG Y R， CHEN J Q， et al. More fidelity， more accurate， more efficient： Progress on numerical simulations for hypersonic flow［J］. Acta Aeronautica et Astronautica Sinica， 2015， 36（1）： 120-134 （in Chinese）.
[10]	蒋浩，柳军，王君媛，等. 全隐LU-SGS算法在高超声速热化学非平衡流刚性问题中的应用［J］. 国防科技大学学报， 2022， 44（2）： 1-8.
	JIANG H， LIU J， WANG J Y， et al. Fully implicit LU-SGS algorithms applied to stiff problems in hypersonic thermochemical non-equilibrium flows［J］. Journal of National University of Defense Technology， 2022， 44（2）： 1-8 （in Chinese）.
[11]	党冠麟，刘世伟，胡晓东，等. 基于CPU/GPU异构系统架构的高超声速湍流直接数值模拟研究［J］. 数据与计算发展前沿， 2020， 2（1）： 105-116.
	DANG G L， LIU S W， HU X D， et al. Direct numerical simulation of hypersonic turbulence based on CPU/GPU heterogeneous system architecture［J］. Frontiers of Data & Computing， 2020， 2（1）： 105-116 （in Chinese）.
[12]	刘君，董海波，刘瑜. 化学非平衡流动解耦算法的回顾与新进展［J］. 航空学报， 2018， 39（1）： 021090.
	LIU J， DONG H B， LIU Y. Review and recent advances in uncoupled algorithms for chemical non-equilibrium flows［J］. Acta Aeronautica et Astronautica Sinica， 2018， 39（1）： 021090 （in Chinese）.
[13]	赵法明. 高超声速空气化学非平衡流与燃气喷流混合反应流场数值模拟研究［D］. 南京：南京航空航天大学， 2019.
	ZHAO F M. A numerical investigation for the mixed reacting flowfield of the air chemical nonequilibrium flow and gaseous jet flow［D］. Nanjing： Nanjing University of Aeronautics and Astronautics， 2019 （in Chinese）.
[14]	HU S Y， JIANG C W， GAO Z X， et al. Zonal disturbance region update method for steady compressible viscous flows［J］. Computer Physics Communications， 2019， 244： 97-116.
[15]	WANG L， DISKIN B， NIELSEN E J， et al. Improvements in iterative convergence of FUN3D solutions［C］∥ AIAA Scitech 2021 Forum. Reston： AIAA， 2021.
[16]	粟虹敏. 可压缩化学反应流动高精度数值方法研究［D］. 西安：西北工业大学， 2021.
	SU H M. Investigation on the high accuracy numerical methods for compressible chemically reacting flows［D］. Xi’an： Northwestern Polytechnical University， 2021 （in Chinese）.
[17]	陈坚强. 国家数值风洞（NNW）工程关键技术研究进展［J］. 中国科学：技术科学， 2021， 51（11）： 1326-1347.
	CHEN J Q. Advances in the key technologies of Chinese national numerical windtunnel project［J］. Scientia Sinica （Technologica）， 2021， 51（11）： 1326-1347 （in Chinese）.
[18]	李鹏，陈坚强，丁明松，等. 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.
	LI P， CHEN J Q， DING M S， et al. Framework design of NNW-HyFLOW hypersonic flow simulation software［J］. Acta Aeronautica et Astronautica Sinica， 2021， 42（9）： 625718 （in Chinese）.
[19]	李鹏，陈坚强，丁明松，等. 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.
	LI P， CHEN J Q， DING M S， et al. Simulation of aerothermal effects on reentry capsule geometry in LENS wind tunnel tests［J］. Acta Aeronautica et Astronautica Sinica， 2021， 42（S1）： 726400 （in Chinese）.
[20]	李鹏，陈坚强，丁明松，等. 高超飞行器热化学非平衡及稀薄滑移流动模拟［J］. 北京航空航天大学学报， 2024， 50（11）： 3391-3401.
	LI P， CHEN J Q， DING M S， et al. Simulaton of therochemical nonequilibrium and rarefied-slip flows for hypersonic flight vehicles［J］. Journal of Beijing University of Aeronautics and Astronautics， 2024， 50（11）： 3391-3401 （in Chinese）.
[21]	高振勋，蒋崇文，李椿萱. 高超高焓非平衡流动数值模拟方法研究综述［J］. 力学进展， 2023， 53（3）： 561-591.
	GAO Z X， JIANG C W， LI C X. Review of numerical simulation methods for hypersonic and high-enthalpy non-equilibrium flow［J］. Advances in Mechanics， 2023， 53（3）： 561-591 （in Chinese）.
[22]	DUNN M G， KANG S W. Theoretical and experimental studies of reentry plasmas： NASA-CR-2232［R］. Washington， D.C.： NASA， 1973.
[23]	PARK C. Review of chemical-kinetic problems of future NASA missions. I： Earth entries［J］. Journal of Thermophysics and Heat Transfer， 1993， 7（3）： 385-398.
[24]	GUPTA R N， YOS J M， THOMPSON R A， et al. A review of reaction rates and thermodynamic and transport properties for an 11-species air model for chemical and thermal nonequilibrium calculations to 30000 K： NASA-RP-1232［R］. Washington， D.C.： NASA， 1990.
[25]	SURZHIKOV S T， SHANG J S. Kinetic models analysis for super-orbital aerophysics： AIAA-2008-1278［R］. Reston： AIAA， 2008.
[26]	王源杰. 考虑多振动温度模型的高温气体效应数值模拟研究［D］. 长沙：国防科学技术大学， 2016： 1-90.
	WANG Y J. Research of numerical calculation methods based on multi-vibrational temperature model in high-temperature conditions［D］. Changsha： National University of Defense Technology， 2016： 1-90 （in Chinese）.
[27]	徐丹，曾明，张威，等. 采用态-态模型的热化学非平衡喷管流数值研究［J］. 计算物理， 2014， 31（5）： 531-538.
	XU D， ZENG M， ZHANG W， et al. Numerical study of thermochemical nonequilibrium nozzle flow in state-to-state model［J］. Chinese Journal of Computational Physics， 2014， 31（5）： 531-538 （in Chinese）.
[28]	KEE R J， RUPLEY F M， MEEKS E， et al. CHEMKIN-III： A FORTRAN chemical kinetics package for the analysis of gas-phase chemical and plasma kinetics： SAND96-8216［R］. Washington， D.C.： USDOE Office of Energy Research， 1996.
[29]	CAPITELLI M， COLONNA G， GIORDANO D， et al. Tables of internal partition functions and thermodynamic properties of high-temperature Mars-atmosphere species from 50K to 50000K： ESA STR-246［R］. Paris： European Space Agency， 2005.
[30]	郝佳傲. 高超声速热化学非平衡耦合效应的建模研究［D］. 北京：北京航空航天大学， 2018： 1-148.
	HAO J A. Modeling of thermochemical nonequilibrium coupling effects in hypersonic flows［D］. Beijing： Beihang University， 2018： 1-148 （in Chinese）.
[31]	董维中. 热化学非平衡效应对高超声速流动影响的数值计算与分析［D］. 北京：北京航空航天大学， 1996： 1-206.
	DONG W Z. Numerical simulation and analysis of thermochemical nonequilibrium effects at hypersonic flow［D］. Beijing： Beihang University， 1996： 1-206 （in Chinese）.
[32]	BLOTTNER F G. Prediction of electron density in the boundary layer on entry vehicles with ablation［C］∥ Fourth Plasma Sheath Symposium. Washington， D.C.： NASA， 1971.
[33]	曾明. 高焓风洞流场测量的数值重建和非平衡效应的数值分析［D］.北京：中国科学院力学研究所， 2006.
	ZENG M. Numerical rebuilding of free-stream measurement and analysis of none-equilibrium effects in high enthalpy tunnel［D］. Beijing： Institute of Mechanics， Chinese Academy of Science， 2006 （in Chinese）.
[34]	丁明松，刘庆宗，江涛，等. 高温气体效应对高超声速磁流体控制的影响［J］. 航空学报， 2020， 41（2）： 123278.
	DING M S， LIU Q Z， JIANG T， et al. Impact of high temperature gas effect on hypersonic magnetohydrodynamic control［J］. Acta Aeronautica et Astronautica Sinica， 2020， 41（2）： 123278 （in Chinese）.
[35]	丁明松，江涛，董维中，等. 热化学模型对高超声速磁流体控制数值模拟影响分析［J］. 物理学报， 2019， 68（17）： 174702.
	DING M S， JIANG T， DONG W Z， et al. Numerical analysis of influence of thermochemical model on hypersonic magnetohydrodynamic control［J］. Acta Physica Sinica， 2019， 68（17）： 174702 （in Chinese）.

模型	总单步耗时/s	源项及其矩阵、能量函数与输运系数的单步耗时/s	计算耗时占比/%
5N_14R_1T	0.749 2	0.325 04	43.38
7N_19R_1T	1.018 6	0.489 39	48.05
11N_22R_1T	1.473 5	0.742 80	50.41
11N_48R_1T	1.913 9	1.178 07	61.55
11N_48R_2T	2.720 7	1.687 84	62.04

模型	综合耗时/s		自适应方法性能
模型	传统方法	自适应方法	时间减少/%	效率提升/%
Prak5_1T	7 197.8	5 781.7	19.67	24.49
Prak7_1T	10 895.6	8 380.15	23.09	30.02
Prak11_2T	26 924.4	17 035.2	36.73	58.05

Adaptive relaxation coupling simulation method for thermochemical non-equilibrium flow

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