Aerodynamic heat calculation method considering surface quality injection effect

Abstract

The invention discloses an aerodynamic heat calculation method considering a surface quality injection effect. The method comprises the following steps: S1, obtaining a geometric shape of a hypersonic aircraft; S2, performing grid division on the obtained geometric shape of the hypersonic aircraft; S3, obtaining hypersonic velocity incoming flow velocity data, hypersonic velocity incoming flow temperature data, hypersonic velocity incoming flow density data and hypersonic velocity incoming flow pressure data, and inputting surface quality injection gas mass flow rate data and surface quality injection gas temperature data into a computer processor; S4, calculating surface mass injection gas density data, surface mass injection gas speed data, surface mass injection gas pressure data and surface mass injection gas temperature data; and S5, calculating wall surface heat flow data of the hypersonic aircraft, and expressing the aerodynamic heat environment of the hypersonic aircraft through the wall surface heat flow data. The aerodynamic thermal environment of the hypersonic aircraft containing surface quality ejection can be predicted more accurately.

Description

technical field [0001] The invention relates to the field of aerodynamic heat and heat protection, and more specifically, relates to an aerodynamic heat calculation method considering the surface mass ejection effect. Background technique [0002] Hypersonic vehicles face a severe aerodynamic thermal environment, and researchers use various thermal protection methods to break through the thermal barrier. Among various thermal protection methods, ablation heat protection technology has been widely used for decades; and sweat cooling technology is expected to solve the thermal protection problem of hypersonic aircraft in adjacent space due to its unique advantages. The above two thermal protection technologies both involve surface mass injection: for example, pyrolysis, evaporation / sublimation and various chemical reactions in the ablation thermal protection technology include the phenomenon of gas precipitation from the surface of the material into the flow field and sweating...

AI Technical Summary

Problems solved by technology

1. Summarize the calculation method of engineering experience. Although the calculation speed is fast, it cannot explore the detailed influence of the surface mass ejection on the hypersonic vehicle on the aerodynamic thermal environment;

2. Only the influence of vertical surface jet flow in hypersonic vehicle surface mass ejection phenomenon is considered, but the influence of parallel surface flow viscosity is not considered;

3. When processing the surface data of the model during the calculation process, only the normal velocity of the surface mass ejection gas is used to simulate the vertical surface jet flow in the surface mass ejection, at the grid points of the wall and the first layer of grid points adjacent to the wall The pressure gradient between them is zero, which cannot truly reflect the surface mass ejection effect, etc.

[0004] In summary, the existing aerothermal calculation methods considering the surface mass injection effect have the problems of single consideration phenomenon and inaccurate and imprecise prediction phenomena

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