电弧风洞高焓流场模拟与气动热校核研究

doi:10.13675/j.cnki.tjjs.190263

推进技术 ›› 2020, Vol. 41 ›› Issue (4): 916-924.DOI: 10.13675/j.cnki.tjjs.190263

电弧风洞高焓流场模拟与气动热校核研究

罗万清^1,2，梁剑寒¹，杨远剑^2,3，孙海浩²，赵金山²

1.国防科技大学高超声速冲压发动机技术重点实验室，湖南长沙 410073;2.中国空气动力研究与发展中心超高速空气动力研究所，四川绵阳 621000;3.哈尔滨工业大学航天学院，黑龙江哈尔滨 150080

发布日期:2021-08-15
作者简介:罗万清，博士生，工程师，研究领域为气动热与热防护技术。E-mail：wtsluo@163.com

Study on High Enthalpy Flowfield Simulation and Aerothermal Verification in Arc-Heated Wind Tunnel

1.Science and Technology on Scramjet Laboratory,National University of Defense Technology,Changsha 410073,China;2.Hypervelocity Aerodynamics Institute,China Aerodynamics Research and Development Center,Mianyang 621000,China;3.School of Astronautics,Harbin Institute of Technology,Harbin 150080,China

Published:2021-08-15

摘要/Abstract

摘要： 为了在电弧风洞更好地开展高超声速飞行器防热材料或结构热考核试验，基于有限体积离散，建立了针对电弧风洞高焓试验状态的多组分热化学非平衡流场数值模拟方法。针对中国空气动力研究与发展中心20MW电弧风洞不同试验模型的高焓流场进行了模拟，获得了试验状态的流场特性和模型表面热流分布，通过与试验测量值比较验证了计算方法。研究发现在喷管出口和试验模型之间的轴向距离很近的情况下，可以采用喷管流场和模型绕流分开模拟。通过对比数值模拟方法中的热化学模型，表明采用Gupta 7组分和5组分空气化学反应数据获得的模型表面热流非常接近，同时相比单温度模型结果，双温度模型结果与试验测量结果更接近。比较了多个状态条件下计算和试验测量获得的试验模型表面热流，发现二者相差都在15%以内，验证了建立的数值方法模拟该风洞高焓流场的可靠性。

关键词: 电弧风洞;热考核试验;高焓状态;数值模拟;热化学非平衡

Abstract: In order to better carry out thermal assessment test of protection materials or structures of hypersonic aircraft in the arc-heated wind tunnel, based on the finite volume discretization, a numerical simulation method for solving the multi-component thermochemical non-equilibrium flowfield was established for the high enthalpy test state. The high enthalpy flowfield was simulated for different test models in the 20MW arc-heated wind tunnel at the China Aerodynamics Research and Development Center (CARDC), and the flowfield characteristics and the heat flux on the model surface were obtained. The calculation method was verified by comparison with the experimental datas. It is found that in the case where axial distance between the nozzle outlet and the test model is very close, the nozzle flowfield and the model flow can be separately simulated. The obtained heat flux on the model surface is very close by using the Gupta’s 7 species and 5 species air chemical reaction data, and the results using double temperature model are closer to the experimental measurement results than the single temperature model. The surface heat flux of the test model obtained by calculation and experimental measurement under multiple state conditions was compared, and the difference between the two is within 15%. The reliability of the numerical method for simulating the flowfield of this wind tunnel was verified.

Key words: Arc-heated wind tunnel;Thermal assessment test;High enthalpy state;Numerical simulation;Thermochemical non-equilibrium

罗万清，梁剑寒，杨远剑，孙海浩，赵金山. 电弧风洞高焓流场模拟与气动热校核研究[J]. 推进技术, 2020, 41(4): 916-924.

LUO Wan-qing^1,2, LIANG Jian-han¹, YANG Yuan-jian^2,3, SUN Hai-hao², ZHAO Jin-shan². Study on High Enthalpy Flowfield Simulation and Aerothermal Verification in Arc-Heated Wind Tunnel[J]. Journal of Propulsion Technology, 2020, 41(4): 916-924.

参考文献

[1] Sheeley J. Arc-Heated Wind Tunnel Failure Prediction Using Artificial Neural Networks[R]. AIAA 2005-898.
[2] Candler G V. The Computation of Weakly Ionized Hypersonic Flows in Thermochemical Nonequilibrium[D]. Stanford： Stanford University, 1988.
[3] Park C. Nonequilibrium Hypersonic Aerothermodynamics[M]. New York： John Wiley and Sons, 1990.
[4] Heinbockel J H， Landry J G. Nozzle Flow with Vibrational Nonequilibrium[R]. NASA-CR-199244， 1995.
[5] Park C， Lee S H. Validation of Multi-Temperature Nozzle Flow Code[J]. Journal of Thermophysics and Heat Transfer， 1995， 9(1): 9-16.
[6] Abe K， Kameyama T， Kihara H， et al. Computation and Experiment of Nonequilibrium Nozzle Flow of Arc-Heated Air[J]. Journal of Thermophysics and Heat Transfer， 2005， 19(4): 428-434.
[7] G?k?en T， Balboni J， Alunni A I. Computational Simulations of the 10MW TP3 Arc-Jet Facility Flow[R]. AIAA 2015-3103.
[8] Düzel ümran， Schroeder Olivia， Huaibao Zhang， et al. Computational Prediction of NASA Langley HYMETS Arc Jet Flow with KATS[R]. AIAA 2018-1719.
[9] 程晓丽，王强，马汉东. 电弧风洞内球锥全目标绕流场计算分析[J]. 空气动力学学报， 2005， 23(3): 279-293.
[10] Nawaz Anuscheh， Drive David M， Imelda Terrazas-Salinas Steve Sepka. Surface Catalysis and Oxidation on Stagnation Point Heat Flux Measurements in High Enthalpy Arc Jets[R]. AIAA 2013-3138.
[11] Scalabrin L C. Numerical Simulation of Weakly Ionized Hypersonic Flow over Reentry Capsules[D]. Ann Arbon： University of Michigan， 2007.
[12] Gupta R N， Yos J M， Thompson R A. A Review of Reaction Rates and Thermodynamic and Transport Properties for the 11-Species Air Model for Chemical and Thermal Nonequilibrium Calculations to 30000K[R]. NASA-TM-101528， 1989.
[13] Lee J H. Basic Governing Equations for the Flight Regimes of Aeroassisted Orbital Transfer Vehicles[R]. AIAA 84-1729.
[14] Blottner F G， Johnson M， Ellis M. Chemically Reacting Viscous Flow Program for Multi-Component Gas Mixtures[R]. Albuquerque： Sandia Laboratories， 1971.
[15] Wilke C R. A Viscosity Equation for Gas Mixtures[J]. Journal of Chemical Physics， 1950， 18(4): 517-519.
[16] MacCormack R W， Canlder G V. The Solution of the Navier-Stokes Equations Using Gauss-Seidel Line Relaxation[J]. Computers & Fluids， 1989， 17(1): 135-150.
[17] 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.
[18] 柳军，刘伟，曾明，等. 高超声速三维热化学非平衡流场的数值模拟[J]. 力学学报， 2003， 35(6): 730-734.

电弧风洞高焓流场模拟与气动热校核研究

Study on High Enthalpy Flowfield Simulation and Aerothermal Verification in Arc-Heated Wind Tunnel

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