高温燃气热环境加热特性的试验方法研究

Numerical Analysis of Thermal Characteristics of High Temperature-gas Thermal Environment

简述了利用高温燃气流引射常温空气对近空间高超声速飞行器头锥部件进行地面热环境模拟的实验方法,试验段高温燃气流引射常温空气使飞行器头锥部件达到驻点附近区域高温而其余蒙皮表面低温的高超声速气动热分布特点。应用CFD计算流体力学软件FLUENT对试验段头锥试件表面的流动加热特性进行了数值分析,得到了高温燃气引射常温空气在不同试验设计条件下试件表面温度分布特点。数值模拟计算结果与飞行器在高超声速飞行状态下对应机体部位气动热的理论计算值进行对比,证实利用高温燃气进行热环境模拟的方法是可行的,为相关的热环境地面模拟设备方案论证提供依据。

An experimental method using high temperature gas flow to simulate aerodynamic thermal environment of hypersonic vehicles is introduced.In the test section of the experiment equipment,a high temperature gas flow is ejected into room temperature air to make heat distribution of the experimental condition in line with that of the real flight condition on the cap.The gas flow and heating characteristics of the experimental equipment are simulated using CFD software FLUENT.Numerical simulation results verify of the experimental method and provide basis for further demonstration of high-temperature-gas thermal environment ground experiment facilities.