高温燃气风洞加热特性仿真分析

姚峰; 董素君; 王浚

高温燃气风洞加热特性仿真分析

北京航空航天大学航空科学与工程学院, 北京 100191

详细信息

中图分类号: V 216.5⁺1
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出版历程
- 收稿日期: 2010-03-10
- 网络出版日期: 2011-06-30

Numerical analysis of high-temperature-gas wind tunnel thermal characteristics

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

摘要

摘要: 提出了利用亚音速高温燃气流进行近空间高超飞行器热环境地面模拟的试验方案,在试验装置试验段,通过高温高速的燃气流引射低速的冷气流,达到仅使飞行器头锥驻点附近区域产生局部高温而其余头锥蒙皮表面低温的目的.对某型高超音速飞行器的头锥利用高温燃气进行加热并利用CFD(Computational Fluid Dynamics)方法对13种模拟工况进行了数值仿真分析.将数值模拟计算结果与飞行器在高超音速飞行状态下对应机体部位气动热的理论计算值进行了对比,证实了亚声速高温燃气热环境模拟方法的可行性,为高温燃气地面模拟设备技术方案论证提供了依据.
- 近空间 /
- 热环境 /
- 高超音速飞行器 /
- 高温燃气 /
- 数值仿真
Abstract: An experimental method using subsonic high-temperature gas flow to simulate aerodynamic thermal environment of near space hypersonic vehicle was introduced. In the test section of the experiment equipment, the room temperatwe air was ejected by the subsonic high-temperature gas flow to make the heat distribution of the experimental condition in line with that of the real flight condition on the cap. 13 experimental conditions were analyzed using computational fluid dynamics(CFD). The numerical analysis verifies the feasibility of the experimental method and provides basis for demonstration of the experiment facilities.
- near space /
- thermal environment /
- hypersonic aricraft /
- high-temperature-gas /
- numerical simulation

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参考文献(1)

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