高超音速飞行器头罩气动热流场数值模拟

Numerical simulation of aerothermal calculation of hypersonic vehicle

对几种不同外形的高超音速飞行器头部气动热效应进行数值模拟,采用Fluent软件对各飞行器进行三维薄层N-S方程数值计算,得到了不同外形的高超音速飞行器头罩外表面热流场分布.然后将计算结果与美国宇航局的超音速飞行器X33模型风洞实验结果进行分析和比较.分析表明:在五倍音速近地飞行时,其中两种外形头部的高超音速飞行器安装中波红外光学成像探测器制导是比较适合的.

The method for the aerothermal calculation of hypersonic vehicle was studied. Temperature of hypersonic vehicle was calculated with the engineering prediction software-Fluent on the basis of three dimension thin layer N-S equation. The aerothermal calculations of different head caps of vehicles were done. The results indicated that two sorts of vehicles can be controlled and guided by infrared ray detected system.