高温燃气热环境模拟方案仿真研究

提出了利用亚声速高温燃气流进行近空间高超声速飞行器气动热环境地面模拟的试验方法,在试验装置试验段,亚声速高温燃气流引射常温空气,使试验中头锥温度分布符合某高超声速飞行状态下气动热分布的规律;应用FLUENT对12种试验工况进行了数值分析,计算结果表明此设备方案下头锥驻点温度低于燃气温度,改变设备引射比可以实现试件后部区域温度的大范围调节,设备可以在一定精度内对高超飞行器相关部件进行气动热环境模拟.

Numerical analysis of subsonic high-temperature-gas thermal environment simulation

The article introduced an experimental method using subsonic high-temperature-gas flow to simulate aerodynamic thermal environment of near space hypersonic vehicle.In the test section of the experiment equipment,the subsonic high-temperature gas flow ejected the room temperature air to make the heat distribution of the experimental condition in line with that of the real flight condition on the surface of the cap.Twelve experimental conditions were analyzed using FLUENT.The numerical analysis shows the temperature of the stagnation will below that of the gas flow,the inject ratio change of the facility can make a wide temperature change in the back region of the nose cone,so the facility is efficient to simulate the aerothermal environment of the hypersonic vehicle in a certain accuracy.