Prediction of Hypersonic Vehicle Reentry Flowfields in Multiple Cases

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Prediction of Hypersonic Vehicle Reentry Flowfields in Multiple Cases

更新时间：2025-07-09

- Prediction of Hypersonic Vehicle Reentry Flowfields in Multiple Cases
- Vol. 44, Issue 1, Pages: 71-76(2010)
- 作者机构：
  
  北京理工大学宇航学院,北京,100081
- 作者简介：
- 基金信息：
- DOI：
  CLC： V19
- Online First：10 January 2010，
  
  Published：2010
- 稿件说明：
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Prediction of Hypersonic Vehicle Reentry Flowfields in Multiple Cases[J]. 2010, 44(1): 71-76.
DOI：

Prediction of Hypersonic Vehicle Reentry Flowfields in Multiple Cases[J]. 2010, 44(1): 71-76. DOI：

摘要

为了弄清典型高超声速飞行器再入时处于连续区的流场状态

采用多组分、考虑非平衡态气体振动激发与化学反应过程的守恒型Navier-Stokes方程组

并用高分辨率TVD格式进行求解

获得了不同飞行工况下飞行器流场的气动热力学(尤其是壁面热流密度)和热-化学非平衡态特性

数值结果与风洞试验及飞行数据吻合较好.通过对多个工况点下流场状态的分析与对比

给出了高超声速飞行器在整个再入过程中的壁面热流密度值、气动力系数

尤其是计算域内热力学非平衡区的分布特性

这对有效地完成飞行器热防护设计具有积极意义.

Abstract

Several typical hypersonic vehicle flowfields are simulated by using the conservation form of Navier-Stokes equations with multi-species

nonequilibrium molecular thermal excitation and chemical reactions based on the high-resolution TVD scheme. The aerothermodynamic properties(such as convective heat flux)and the thermo-chemical nonequilibrium phenomenon of hypersonic-continuum flowfields are obtained during reentry trajectory

and these results are in good agreement with experiment and flight data. By analyzing and comparing the difference of the hypersonic vehicle reentry flowfields in multiple cases

the predictive results

such as wall heat flux

aerodynamic-force coefficients

particularly the thermal nonequilibrium areas in the computational domain

are achieved to benefit the design of vehicle thermal protection system.

关键词

Keywords

references

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WANG Jun, WANG Peiguang. Integrated thermal protection and control design methodology for hypersonic vehicles[J]. Journal of Beijing University of Aeronautics and Astronautics, 2006, 32(10): 1129-1134.

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