高温化学非平衡湍流边界层直接数值模拟

doi:10.7527/S1000-6893.2020.24877

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

高温化学非平衡湍流边界层直接数值模拟

刘朋欣^1,2, 袁先旭^1,2, 孙东^1,2, 傅亚陆^1,2, 李辰^1,2

1. 中国空气动力研究与发展中心空气动力学国家重点实验室, 绵阳 621000;
2. 中国空气动力研究与发展中心计算空气动力研究所, 绵阳 621000

收稿日期:2020-10-15 修回日期:2020-11-16 出版日期:2022-01-15 发布日期:2022-02-14
通讯作者: 李辰 E-mail:lichen@skla.cardc.cn
基金资助:
国家重点研发计划（2019YFA0405201）；国家数值风洞工程

Direct numerical simulation of high-temperature turbulent boundary layer with chemical nonequilibrium

LIU Pengxin^1,2, YUAN Xianxu^1,2, SUN Dong^1,2, FU Yalu^1,2, LI Chen^1,2

1. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China;
2. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received:2020-10-15 Revised:2020-11-16 Online:2022-01-15 Published:2022-02-14
Supported by:
National Key R & D Program of China (2019YFA0405201); National Numerical Windtunnel Project

摘要/Abstract

摘要： 高超声速飞行器在特定工况下飞行时，其表面会存在湍流与化学非平衡耦合作用，但考虑化学反应的高温湍流边界层的研究工作还十分有限。选取高超声速楔形体头部斜激波后的流动状态，分别采用热完全气体模型、空气化学反应模型开展直接数值模拟（DNS）研究，对比分析了化学非平衡效应对湍流统计量、湍流脉动量的影响趋势，并研究了高温湍流边界层标度律。计算结果表明，以吸热离解反应为主的化学非平衡效应会使边界层平均温度和脉动温度显著降低，但对平均速度剖面、速度脉动、雷诺应力的影响较小；在高温化学非平衡湍流边界层的对数区，各流动参数的拓展自相似理论的相对标度指数基本符合标度律。

关键词: 高超声速流动, 高温, 化学非平衡, 湍流边界层, 直接数值模拟, 标度律

Abstract: Under specific flying conditions, interaction between turbulence and chemical nonequilibrium will occur on hypersonic vehicle surfaces; however, related research is limited. Choosing the flow state after the leading shock of a cone and utilizing two gas models, i.e. the calorically perfect gas and the chemical reaction gas, we conduct a Direct Numerical Simulation (DNS) study to analyze the effects of chemical nonequilibrium on the turbulence statistics and fluctuations, and investigate the scaling law. The results show that the endothermic dissociated reaction is dominant in the boundary layer, significantly reducing the average temperature and temperature fluctuation. However, chemical nonequilibrium only have a small influence on the average streamwise velocity, velocity fluctuation and Reynold stress. In the log-region, the Extended Self-Similarity(ESS) of the fluctuations is still consistent with the scaling law.

Key words: hypersonic flow, high-temperature, chemical nonequilibrium, turbulent boundary layer, DNS, scaling law

中图分类号:

V211.3

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.

LIU Pengxin, YUAN Xianxu, SUN Dong, FU Yalu, LI Chen. Direct numerical simulation of high-temperature turbulent boundary layer with chemical nonequilibrium[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022, 43(1): 124877.

参考文献

[1] MOIN P, MAHESH K. DIRECT NUMERICAL SIMULATION: A tool in turbulence research[J]. Annual Review of Fluid Mechanics, 1998, 30(1): 539-578.
[2] PIROZZOLI S. Numerical methods for high-speed flows[J]. Annual Review of Fluid Mechanics, 2011, 43: 163-194.
[3] 李新亮. 高超声速湍流直接数值模拟技术[J]. 航空学报, 2015, 36(1): 147-158. LI X L. Direct numerical simulation techniques for hypersonic turbulent flows[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1): 147-158(in Chinese).
[4] 孙东, 刘朋欣, 童福林. 展向振荡对激波/湍流边界层干扰的影响[J]. 航空学报, 2020, 41(12): 124054. SUN D, LIU P X, TONG F L. Effect of spanwise oscillation on interaction of shock wave and turbulent boundary layer[J]. Acta Aeronautica et Astronautica Sinica, 2020, 41(12): 124054(in Chinese).
[5] 孙东, 刘朋欣, 沈鹏飞, 等. 马赫6 柱-裙激波/边界层干扰直接模拟研究[J]. 航空学报, 2021, 42(6): 124681. SUN D, LIU P X, SHEN P F, et al. Direct numerical simulation of shock wave/turbulent boundary layer interaction in a hollow cylinder-flare configuration at Ma 6[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(6): 124681(in Chinese).
[6] MARTÍN M P, WEIRS V G, CANDLER G V. DNS of reacting hypersonic turbulent boundary layer[C]//29th AIAA Fluid Dynamics Conference. Reston: AIAA, 1998.
[7] PIN M, CANDLER G. DNS of a Mach 4 boundary layer with chemical reactions[C]//38th Aerospace Sciences Meeting and Exhibit. Reston: AIAA, 2000.
[8] MARTÍN M, CANDLER G. Temperature fluctuation scaling in reacting boundary layers[C]//15th AIAA Computational Fluid Dynamics Conference. Reston: AIAA, 2001.
[9] MARTÍN M P. Exploratory study of turbulence/chemistry interaction in hypersonic flows[C]//36th AIAA Thermophysics Conference. Reston: AIAA, 2011.
[10] DUAN L, MARTÍN M P. Effect of finite-rate chemical reactions on turbulence in hypersonic turbulence boundary layers[C]//47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition. Reston: AIAA, 2009.
[11] DUAN L, MARTÍN M P. Procedure to validate direct numerical simulations of wall-bounded turbulence including finite-rate reactions[J]. AIAA Journal, 2009, 47(1): 244-251.
[12] DUAN L, MARTÍN P. Study of turbulence-chemistry interaction in hypersonic turbulent boundary layers[C]//20th AIAA Computational Fluid Dynamics Conference. Reston: AIAA, 2011.
[13] DUAN L, MARTÍN M P. Direct numerical simulation of hypersonic turbulent boundary layers. Part 4. Effect of high enthalpy[J]. Journal of Fluid Mechanics, 2011, 684: 25-59.
[14] CASTRO M, COSTA B, DON W S. High order weighted essentially non-oscillatory WENO-Z schemes for hyperbolic conservation laws[J]. Journal of Computational Physics, 2011, 230(5): 1766-1792.
[15] 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-TM-101528[R]. Washington, D.C.: NASA, 1990.
[16] LEHR H F. Experiments on shock-induced combustion[J]. Aeronautica Acta, 1972, 17: 589-597.
[17] 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).
[18] 刘朋欣. 旋转爆震复杂流场的高精度数值模拟与机理分析[D]. 北京: 军事科学院, 2018: 43-51. LIU P X. High-order numerical simulation and mechanism study of complex flow in rotating detonation[D]. Beijing: Academy of Military Sciences PLA China, 2018: 43-51(in Chinese).
[19] LI Q, LIU P X, ZHANG H X. Further investigations on the interface instability between fresh injections and burnt products in 2-D rotating detonation[J]. Computers & Fluids, 2018, 170: 261-272.
[20] LIU P X, LI Q, HUANG Z F, et al. Interpretation of wake instability at slip line in rotating detonation[J]. International Journal of Computational Fluid Dynamics, 2018, 32(8-9): 379-394.
[21] LIU P X, GUO Q L, SUN D, et al. Wall effect on the flow structures of three-dimensional rotating detonation wave[J]. International Journal of Hydrogen Energy, 2020, 45(53): 29546-29559.
[22] KNIGHT D, LONGO J, DRIKAKIS D, et al. Assessment of CFD capability for prediction of hypersonic shock interactions[J]. Progress in Aerospace Sciences, 2012, 48-49: 8-26.
[23] MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8): 1598-1605.
[24] ADLER M C, GONZALEZ D R, STACK C M, et al. Synthetic generation of equilibrium boundary layer turbulence from modeled statistics[J]. Computers & Fluids, 2018, 165: 127-143.
[25] DUAN L, BEEKMAN I, MARTÍN M P. Direct numerical simulation of hypersonic turbulent boundary layers. Part 2. Effect of wall temperature[J]. Journal of Fluid Mechanics, 2010, 655: 419-445.
[26] PIROZZOLI S, BERNARDINI M, GRASSO F. Characterization of coherent vortical structures in a supersonic turbulent boundary layer[J]. Journal of Fluid Mechanics, 2008, 613: 205-231.
[27] SUBBAREDDY P, CANDLER G. DNS of transition to turbulence in a hypersonic boundary layer[C]//41st AIAA Fluid Dynamics Conference and Exhibit. Reston: AIAA, 2011.
[28] TIKHOMIROV V M. Local structure of turbulence in an incompressible viscous fluid at very large Reynolds numbers[M]//Selected Works of A.N.Kolmogorov. Dordrecht: Springer Netherlands, 1991: 312-318.
[29] KOLMOGOROV A N. A refinement of previous hypotheses concerning the local structure of turbulence in a viscous incompressible fluid at high Reynolds number[J]. Journal of Fluid Mechanics, 1962, 13(1): 82-85.
[30] BENZI R, CILIBERTO S, TRIPICCIONE R, et al. Extended self-similarity in turbulent flows[J]. Physical Review E, Statistical Physics, Plasmas, Fluids, and Related Interdisciplinary Topics, 1993, 48(1): R29-R32.
[31] SHE Z, LEVEQUE E. Universal scaling laws in fully developed turbulence[J]. Physical Review Letters, 1994, 72(3): 336-339.

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

高温化学非平衡湍流边界层直接数值模拟

Direct numerical simulation of high-temperature turbulent boundary layer with chemical nonequilibrium

RichHTML

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]	樊哲铭, 杨未柱, 曾延, 赵哲南, 李磊. 激光熔覆修复GH4169合金各向异性拉伸性能[J]. 航空学报, 2024, 45(8): 429129-429129.
[2]	刘小勇, 王明福, 刘建文, 任鑫, 张轩. 超燃冲压发动机研究回顾与展望[J]. 航空学报, 2024, 45(5): 529878-529878.
[3]	赖江, 范召林, 王乾, 董思卫, 童福林, 袁先旭. 高超声速有攻角锥裙直接数值模拟[J]. 航空学报, 2024, 45(2): 128610-128610.
[4]	吴忧, 陈兵, 杨庆春, 徐旭. 碳氢燃料超燃冲压发动机热非平衡效应[J]. 航空学报, 2024, 45(11): 529399-529399.
[5]	陈锐达, 陈夏超, 陈泓宇, 徐辉, 洪鑫. 模拟月面高温环境下120 N发动机点火特性和排气试验[J]. 航空学报, 2024, 45(11): 529112-529112.
[6]	曾繁宇, 邱云龙, 曹占伟, 张伦, 陈伟芳. 超声速湍流边界层阵列式微吹气流动控制与减阻特性[J]. 航空学报, 2023, 44(S2): 729396-729396.
[7]	傅亚陆, 袁先旭, 刘朋欣, 余明. 可压缩壁湍流热力学量统计特性分析[J]. 航空学报, 2023, 44(9): 127217-127217.
[8]	王震宇, 王计真, 杨婧艺, 何鹏远, 潘成浩, 周凌波, 何成, 何欢. 基于新型粒子群算法的结构动力学热振模型修正[J]. 航空学报, 2023, 44(7): 226559-226559.
[9]	张阳, 罗佳奇, 曾先. 基于改进虚拟单元浸没边界法的椭圆气动噪声问题[J]. 航空学报, 2023, 44(19): 128418-128418.
[10]	赵楠, 李多生, 叶寅, 刘奋成, 江五贵. 激光选区熔化成形GH5188合金微观组织及性能[J]. 航空学报, 2023, 44(19): 428332-428332.
[11]	陈薄, 贾飞, 马兴裕. 油滴与高温固体壁面碰撞的动态铺展与传热[J]. 航空学报, 2023, 44(17): 128307-128307.
[12]	刘重晓, 王江峰. 滑移流区化学非平衡流中气动热环境的数值模拟[J]. 航空学报, 2023, 44(16): 127980-127980.
[13]	李峻洋, 刘朋欣, 余明, 孙东, 董思卫, 袁先旭. 高焓湍流边界层黏性耗散对壁面热流的影响[J]. 航空学报, 2023, 44(15): 528963-528963.
[14]	刘晓东, 刘朋欣, 李辰, 孙东, 袁先旭. 高焓激波/湍流边界层干扰直接数值模拟[J]. 航空学报, 2023, 44(13): 127832-127832.
[15]	丁博, 陈真利, 焦子涵, 王锦程, 李铮, 白光辉. 脉冲表面电弧放电对高超声速压缩拐角的非定常控制机理[J]. 航空学报, 2023, 44(12): 127744-127744.