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.
用铂膜电阻温度计测量了前向台阶诱导激波与湍流边界层相互作用流场中的表面热流率脉动。
Wall heat transfer fluctuations have been measured using a platinum film resistance thermometer in forward facing steps induced shock wave and turbulent boundary layer interaction fields.
通过采用线线合成光谱的方法得到激波后不同时刻高温空气中OH分子的转动温度。
The rotational temperatures were determined using fits to synthetic OH molecular spectra at different time behind shock waves.
采用实验方法研究了进水温度对汽液两相流激波升压特性的影响。
Through the use of an experimental method the influence of inlet water temperature on the shock wave pressure rise characteristics of steam water two phase flows has been investigated.
同时，还对不同角度内楔的反射激波后气流温度进行了比较。
The temperatures after the reflection of shock wave front with different inner angles are also compared.
采用单、双温度模型两种粘性激波层方程组对弹头驻点区非平衡流场作了数值模拟。
The numerical solutions of VSL equation sets in one-temperature and two-temperature cases are obtained for flows in the stagnation region of a hypervelocity blunt body.
观察到不同的等离子体初始温度会影响靶前激波的形成时间，进而影响质子产额。
It is found that the time required for the shock formation can be affected by the initial plasma temperature, which influences the energetic proton generation in the shock.
观察到不同的等离子体初始温度会影响靶前激波的形成时间，进而影响质子产额。
It is found that the time required for the shock formation can be affected by the initial plasma temperature, which influences the energetic proton generation in the shock.
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