The paper presents the results obtained for the distribution of heat flux incident upon a refractory plate of a hypersonic flight vehicle moving at space velocities at various distances from the Earth’s surface. The paper also provides the results of studying phase transitions in the near-wall boundary layer occurring during the hypersonic flow over the ablating surface. The effect of the catalytic wall on heat flux is analyzed. The emphasis is on the analysis of mass loss from the surface of high-velocity flight vehicles based on detailed consideration of the mechanism of heterogeneous catalytic reactions taking place under the surface mass transfer conditions. A temperature distribution is provided across the thickness of the boundary layer at the stagnation point of a blunt-nosed body with a refractory coating for a specific section of the flight path. The mass loss from the surface of crystalline refractory bodies is determined.

中文翻译：

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超音速流对降解条件下隔热表面熔化速率的影响

本文介绍了以高速度飞行的高超音速飞行器的耐火板上入射的热通量的分布所获得的结果，该高音速飞行器以距地球表面不同距离的速度运动。本文还提供了研究在烧蚀表面上的超音速流动过程中发生的近壁边界层中相变的结果。分析了催化壁对热通量的影响。重点是在详细考虑表面质量转移条件下发生的多相催化反应机理的基础上，分析高速飞行器表面的质量损失。在具有钝化体的钝头体的停滞点处，在边界层的整个厚度上提供了温度分布，并为飞行路径的特定部分提供了耐火涂层。确定了从晶体耐火材料表面的质量损失。