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The results indicate that the thickness variations exhibit no significant influence on stagnation temperature, while the cooling power drops sharply as the thickness increases.
计算结果表明：驻点温度随热防护层厚度的变化并不明显，而冷却系统功率随热防护层厚度增加急剧降低；
In the model the exit area ratio, solid particle mass ratio, fuel enthalpy of combustion, jet gas molecular weight, chamber stagnation temperature, flight Math number etc. have been considered.
在该模型中考虑了底排出口面积比，排气固相颗粒质量比，燃料热值，燃气分子量，燃烧室总温，飞行马赫数等因素。
The temperature profiles measured from the boundary layers at stagnation-point are reasonable in agreement with the results of theoretical calculation.
测得驻点烧蚀边界层的温度分布与相应的理论计算结果符合较好。
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