There are represented research results related to the study of phase transitions in the wall boundary layer occurring during the flow of an ablating surface in a hypersonic stream. The influence of the catalytic wall on the heat flux is considered. The main attention is paid to the analysis of the melting bodies ablation from the surface of high-speed aircraft, based on a detailed recordkeeping of heterogeneous catalytic reactions flow mechanism in surface mass transfer conditions. The distribution of temperature factors over the thickness of the boundary layer at the critical point of the blunted body for a particular flight path segment is given. The ablation from the surface of crystalline bodies is designated. It is shown that the flow of non-Newtonian fluids escapes Newton’s law. Liquids are considered are highly inhomogeneous and consists of large molecules forming complex spatial structures. Moreover, the faster the external impact occurs on the binder macromolecules suspended in a liquid, the higher will be its viscosity. A large temperature gradient is researched within the layer of liquid that forms on the surface of an ablating material. The necessity of simultaneous integration of the entire system of the equation of a liquid layer which consists of equations of continuity, motion and energy together with the dependence of the viscosity coefficient on temperature and tangential stress, is explained.

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