高超声速平板/空气舵热环境数值模拟研究

谭杰; 孙晓峰; 刘芙群; 杨鸿俊; 陈政

doi:10.7638/kqdlxxb-2018.0234

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高超声速平板/空气舵热环境数值模拟研究

专栏——首届中国空气动力学大会青年优秀论文 | 更新时间：2026-05-28

- 高超声速平板/空气舵热环境数值模拟研究
- Numerical simulation of aerodynamic heating environment of a hypersonic plate/rudder configuration
- 空气动力学学报 2019年37卷第1期页码：153-159
- 作者机构：
  
  中国运载火箭技术研究院,北京,100076
- 作者简介：
  
  谭杰(1985-), 男, 湖北公安人, 博士, 高级工程师, 研究方向:飞行器气动与热环境设计.E-mail:tanjie2012@qq.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0234
  中图分类号： V211.1
- 纸质出版：2019
- 稿件说明：
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谭杰, 孙晓峰, 刘芙群, 杨鸿俊, 陈政. 高超声速平板/空气舵热环境数值模拟研究[J]. 空气动力学学报, 2019, 37(1): 153-159.

TAN Jie, SUN Xiaofeng, LIU Fuqun, et al. Numerical simulation of aerodynamic heating environment of a hypersonic plate/rudder configuration[J]. 2019, 37(1): 153-159.
谭杰, 孙晓峰, 刘芙群, 杨鸿俊, 陈政. 高超声速平板/空气舵热环境数值模拟研究[J]. 空气动力学学报, 2019, 37(1): 153-159. DOI： 10.7638/kqdlxxb-2018.0234.

TAN Jie, SUN Xiaofeng, LIU Fuqun, et al. Numerical simulation of aerodynamic heating environment of a hypersonic plate/rudder configuration[J]. 2019, 37(1): 153-159. DOI： 10.7638/kqdlxxb-2018.0234.

摘要

针对高超声速平板/空气舵模型开展了热环境数值模拟研究，重点分析了舵偏角

、舵缝高度

和边界层流态对缝隙内舵轴及干扰区热环境的影响规律。研究结果表明：零舵偏状态缝隙内气流速度为亚声速，热环境可以忽略；舵面偏转时，缝隙入口气流速度和压力显著增大，在

=5°~15°范围内，舵轴及干扰区热环境随舵偏近似线性增长；舵轴及干扰区热流随

增大呈现先上升后缓慢下降的趋势，

从5 mm增大到7 mm时，舵轴热环境增加超过1倍；边界层流态对空气舵缝隙内热环境影响很大，在15°舵偏条件下，层流状态舵轴及干扰区热环境约是湍流的3~5倍，这是因为层流边界层较薄，缝隙内流速更高。

Abstract

This article presents a numerical study to investigate aerodynamic heating environments of a hypersonic plate/rudder configuration. In particular

the effects of the deflection angle

gap displacement

and boundary layer flow pattern on aerodynamic heating environment of the rudder shaft as well as its interaction region were analyzed in detail. The analysis show that the heating environment in the gap is negligible at 0° deflection angle due to the subsonic flow. However

the rudder deflection results in high speed and high pressure flow inside the gap

the thermal loads of the rudder shaft

and its interaction region almost linearly increase with increasing

between 5° and 15°. The heating flux of the rudder shaft and its interaction region increase firstly and then decrease gradually with the increasing

. The heat flux of

=7 mm is nearly two times of that of

=5 mm. In addition

the flow pattern of the boundary layer exerts a significant influence on the heat flux in the gap. In full laminar case

the thermal loads of the rudder shaft and its interaction region are three to five times of those within the full turbulent case under the condition of

=15°. This is because the thinner boundary layer of laminar flow results in high speed flow in the gap.

关键词

Keywords

references

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BABINSKY H, HARVEY J K. Shock wave-boundary-layer interactions[M]. Cambridge University Press, 2011.

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