高温非平衡流地面试验及数值模拟

李俊红; 苗文博; 谌君谋; 程晓丽

doi:10.13224/j.cnki.jasp.20220243

高温非平衡流地面试验及数值模拟

doi: 10.13224/j.cnki.jasp.20220243

李俊红^{1, 2,},
苗文博^{1, 2,*, ,},
谌君谋²,
程晓丽^{1, 2}

1.
中国航天空气动力技术研究院空气动力理论与应用研究所，北京 100074
2.
中国航天科技集团有限公司航天飞行器气动热防护试验室，北京 100048

基金项目: 国家重点研发计划项目（2019YFB1704202）；预研项目（6140206040215）

详细信息

作者简介:
李俊红（1978-），女，研究员，博士，研究方向为高温非平衡流和复杂流动热环境数值计算

通讯作者:
苗文博（1980-），男，研究员，博士，研究方向为高温非平衡流数值计算和实。E-mail：tingles@126.com

中图分类号: V411.3
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- 被引次数: 0
出版历程
- 收稿日期: 2022-04-24
- 网络出版日期: 2023-06-26

Ground test and numerical simulation on high temperature non-equilibrium flow

LI Junhong^{1, 2
,},
MIAO Wenbo^{1, 2,*
, ,},
SHEN Junmou²,
CHENG Xiaoli^{1, 2}

1.
Institute for Aerodynamic Theory and Application， China Academy of Aerospace Aerodynamics，Beijing 100074，China
2.
Laboratory of Aero-thermal Protection Technology for Aerospace Vehicles， China Aerospace Science and Technology Corporation，Beijing 100048，China

摘要

摘要:
基于高温非平衡流动数值计算和试验验证不足的现状，发展了高温流场地面试验模拟技术与流场显示技术。分别在FD-21高焓激波风洞和FD-20常规激波风洞中，开展了高温非平衡流动地面试验，获得了半圆球空间流场结构和气动加热结果。同时，针对典型高超声速飞行环境，建立了高空高超声速热化学非平衡流动数值模拟技术，并利用地面试验对计算方法的可靠性进行了验证，试验模型半径20 mm和60 mm的半圆球。计算结果表明：①风洞来流参数经过数值计算对比验证，其测得的来流压力和组分可以作为后续数值模拟方法的输入条件。②对典型半圆球模型进行了流场数值模拟，并对比分析了半圆球热流试验结果与计算结果。表明双温模型（热化学非平衡模型-2T）计算与试验吻合良好；非催化壁面条件下，总温为2700 K时，2T模型热流计算结果与试验结果的相对误差为11.6%；总温为4050 K时，2T模型热流计算结果与试验结果的相对误差为17.5%。③计算结果获得的试验纹影（圆球脱体激波距离）与吻合良好；非催化壁面条件下，2T模型激波脱体距离与纹影的相对误差为−1.9%～0.86%。
- 高温非平衡 /
- 激波风洞 /
- 地面试验 /
- 激波脱体距离 /
- 数值模拟
Abstract:
Because of the insufficiency of numerical simulation and test verification of high temperature non-equilibrium flow status, the high temperature flow field ground test simulation technology and display technology in high enthalpy shock wave wind tunnel were developed respectively. The ground tests of high temperature non-equilibrium flows were carried out in FD-21 high enthalpy shock wave wind tunnel and FD-20 normal shock wave wind tunnel, then the spatial flow field structure and the aerodynamic heating results of the test hemisphere were obtained. Meanwhile, the numerical simulation technology of high altitude and hypersonic thermochemical non-equilibrium flow was established for the supersonic flight environment, and the reliability of the calculation method was verified by the ground test. The test models were of a hemisphere structure with radius of 20 mm and 60 mm. The calculation results showed that: (1) The inlet flow parameters in the wind tunnel were verified by numerical simulation and the pressure and species can be taken as input parameters for the below numerical simulation. (2) Numerical simulations were carried out on the above typical hemispheres, and the test and calculation results of the hemisphere heat flux were compared and analyzed. The results showed that the two-temperature model (thermal chemical non-equilibrium model-2T) was in good agreement with the test. Under the condition of non-catalytic wall, the relative error between the calculated heat flux result of 2T model and the test result was 11.6% when the total temperature was 2700 K. The relative error was 17.5% when the total temperature was 4050 K. (3) The test schlieren (hemisphere shock wave off distance) obtained from the calculated results was in good agreement with each other. Under the condition of non-catalytic wall, the relative error between the shock wave off distance and schlieren of 2T model was −1.9%−0.86%.
- high temperature non-equilibrium /
- shock wave wind tunnel /
- ground test /
- shock wave off distance /
- numerical simulation

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图 1 FD-21自由活塞高焓激波风洞

Figure 1. FD-21 free piston high enthalpy shock wave wind tunnel

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图 2 纹影系统原理示意图

Figure 2. Schematic diagram of schlieren system principle

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图 3 激光光源和高速相机

Figure 3. Laser light source and high speed camera

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图 4 半径为60 mm半圆球纹影

Figure 4. Radius 60 mm hemisphere schlieren

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图 5 半圆球试验驻点热流

Figure 5. Heat flux at hemisphere stagnation point of test status

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图 6 半径为20 mm半圆球结构网格示意图

Figure 6. Schematic diagram of structure mesh radius 20 mm hemisphere

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图 7 气体模型对半圆球部驻点线温度的影响

Figure 7. Effect of gas models on the temperature along the hemisphere stagnation

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图 8 气体模型对半圆球部驻点线上组分质量分数的影响

Figure 8. Effect of gas models on the species mass fraction along the hemisphere stagnation

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图 9 半圆球z=0 mm对称面平衡特性等值线

Figure 9. Equilibrium performance contour of the hemisphere on the z=0 mm symmetry

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图 10 半圆球对称面z=0 mm上热流分布及其与试验结果的对比

Figure 10. Distribution of the heat flux of the hemisphere on the z=0 mm symmetry and comparison with the test result

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图 11 半圆球z=0 mm对称面压力计算结果与纹影试验结果对比

Figure 11. Comparison of the pressure contour of the hemisphere between the computation and schlieren test on the z=0 mm symmetry plane

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表 1 试验喷管出口流场参数和气体组元质量分数

Table 1. Flow field parameters and gas species mass fraction at the test nozzle exit

工况	总压/ MPa	总温/ K	静压/ Pa	平动-转动温度/K	振动电子温度/K	来流速度/ （m/s）	来流马赫数	质量分数/%				热流试验	纹影试验
工况	总压/ MPa	总温/ K	静压/ Pa	平动-转动温度/K	振动电子温度/K	来流速度/ （m/s）	来流马赫数	N₂	O₂	NO	O	热流试验	纹影试验
1	9.2	2700	240	161	1320	2417	9.78	75.12	21.84	3.04	3.4×10⁻³	√
2	20.3	4050	578	301	1534	3160	9.29	74.17	20.71	5.06	5.2×10⁻³	√	√

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表 2 半圆球驻点热流计算结果与试验结果对比

Table 2. Heat flux of the hemisphere comparison between the computation and test results at stagnation point

工况		试验	Perfect	1T-NC	1T-FC	2T-NC	2T-FC
1	热流数值结果/（MW/m²）	1.25	1.47	1.452	1.453	1.395	1.395
1	（CFD/试验−1）×100%		17.6	16.16	16.24	11.6	11.60
2	热流数值结果/（MW/m²）	2.97	4.52	4.14	4.22	3.49	3.59
2	（CFD/试验−1）×100%		52.2	39.4	42.1	17.5	20.9

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表 3 半圆球脱体激波距离计算结果与试验结果对比（R=60 mm）

Table 3. Comparison of the shock off distance of the hemisphere between the computation results and schlieren test （R=60 mm）

方法	试验	Perfect	1T	2T
$\varDelta_x $/mm	7.02～7.215	8.59	6.48	7.08
相对误差/%	0	19.1～22.3	−10.2～−7.7	−1.9～0.86

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