533.16 Procedure for numerical solution of equations of laminar-turbulent boundary layer on an axially symmetrical blunt body in a jet of combustion gases of liquid-propellant engine

Gorskiy V. V. (Bauman Moscow State Technical University), Kovalsky M. G.


doi: 10.18698/2309-3684-2018-2-96108

Currently, carbon-based materials are widely used as an ablative thermal protection for high-heat constructional elements in air and space en-gineering. In its turn, forecasting a change in shape of external surfaces of the specified elements with the course of time, which is determined by scorching of thermal protection, cannot be separated from the use of calcula-tion and theoretical procedures, which describe course of different phys-ico-chemical and mechanical processes associated with course of the considered event. Thereby, it is mandatory to approve such procedures through the re-sults of experi-mental studies, conducted in jets inside aerodynamic tunnels.
Among primary evidences of ablation of carbon-based materials is erosion (mass loss), which is usually observed in high-pressure gas flows. Meanwhile, it is required to carry out studies on large-scale models in the course of development tests, and that had de-termined the wide use of under-expanded jets of combustion gases of liquid-propellant rocket engines (LPE) for simulation of erosion of thermal protection.
Among the basic problems, encountering during solution of this kind of tasks, is calcu-lation of laminar-turbulent heat exchange in the conditions of gradient flow past blunt-ed point of the tested model by a diverging gas jet. This article is dedicated to the solu-tion of this problem and includes the modified version of semi-empirical model of ap-parent turbulent viscosity, approved by the results of experimental studies. This article shows that the use of this method makes it possible to specify significantly thermal con-di-tions of the model in comparison with the use of effective length method, which is used universally in practical work.

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