本文叙述了用光学法测量小发动机燃气流火焰温度、燃气流中模型前端的激波温度及不同材料的模型表面温度。
This paper presents a no-contact temperature measurement for a small rocket engine jet exhaust, for a shock wave on nose cone of a model in a jet exhaust and for a model surface of various materials.
结果表明，随着磁场的增强，激波脱体距离逐渐增加；总阻力系数和壁面温度逐渐减小。
The results show that the shock standoff distance is increased and total drag coefficient and wall temperature are reduced with increasing external magnetic field.
分析了各种气体模型对激波脱体距离、壁面热流、温度分布和密度分布等的影响。
It is analyzed that the thermal and chemical model have a effect on the shock detached distance, heat transfer rate, the distributions of temperature and density.
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