LENS风洞试验返回器模型气动热特性模拟

doi:10.7527/S1000-6893.2021.26400

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LENS风洞试验返回器模型气动热特性模拟

李鹏^1,2, 陈坚强^1,2, 丁明松^1,2, 梅杰², 何先耀², 董维中²

1. 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:2021-09-01 修回日期:2021-09-23 发布日期:2021-10-14
通讯作者: 董维中 E-mail:dongwz1966@163.com
基金资助:
国家数值风洞工程

Simulation of aerothermal effects on reentry capsule geometry in LENS wind tunnel tests

LI Peng^1,2, CHEN Jianqiang^1,2, DING Mingsong^1,2, MEI Jie², HE Xianyao², DONG Weizhong²

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

Received:2021-09-01 Revised:2021-09-23 Published:2021-10-14
Supported by:
National Numerical Wind tunnel project

摘要/Abstract

摘要： 国家数值风洞高超声速流动模拟软件HyFLOW的研制对打破国外同类软件的技术壁垒具有重要意义。与国外DPLR软件进行了对比研究，同时系统介绍了HyFLOW软件求解器的数值方法、物理化学模型以及壁面催化特性计算模型等主要方法，采用典型算例对有限催化模型进行了数值验证，最后基于LENS风洞试验146 mm返回器标模外形开展了高超声速气动热特性数值模拟。研究结果表明，HyFLOW软件在高超声速热化学非平衡流动模拟与评估方面的气动力计算精度高，与国外同类软件DPLR相当，同时其壁面催化条件下的气动热计算精度可靠，可信度高。

关键词: 高超声速, 热化学非平衡, 国家数值风洞, HyFLOW软件, DPLR软件, LENS激波风洞

Abstract: The development of the National Numerical Windtunnel hypersonic flow simulation software HyFLOW is of huge significance in breaking the technical barriers of similar foreign software. A comparative study with the foreign DPLR software is conducted, and the main methods of the HyFLOW solver such as the numerical method, the physical and chemical models, and the calculation model of the wall catalytic characteristics are systematically introduced. Subsequently, numerical verification of the partial catalytic wall model is executed with a typical example, and finally the numerical simulation of the hypersonic aerothermal characteristics is performed based on the standard 146-mm reentry capsule model in the LENS wind tunnel test. The results show that the HyFLOW software has high aerodynamic calculation accuracy in simulation and evaluation of hypersonic thermochemical non-equilibrium flow, equivalent to that of the similar foreign DPLR software, while the calculation accuracy of aerodynamic heating under the wall catalytic conditions is reliable, with high credibility.

Key words: hypersonic, thermochemical non-equilibrium, National Numerical Wind tunnel, HyFLOW, DPLR, LENS shock tunnel

中图分类号:

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.

LI Peng, CHEN Jianqiang, DING Mingsong, MEI Jie, HE Xianyao, DONG Weizhong. Simulation of aerothermal effects on reentry capsule geometry in LENS wind tunnel tests[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(S1): 726400-726400.

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E-mail：hkxb@buaa.edu.cn

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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

LENS风洞试验返回器模型气动热特性模拟

Simulation of aerothermal effects on reentry capsule geometry in LENS wind tunnel tests

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