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Aerothermal Calculation Method Considering Surface Mass Ejection Effect
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A surface quality and calculation method technology, applied in calculation, computer-aided design, design optimization/simulation, etc., can solve the problem of not being able to explore the influence of surface quality ejection aerodynamic and thermal environment details, not considering the influence of parallel surface flow viscosity, and considering single phenomena And other issues
Active Publication Date: 2022-02-11
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology
[0004] 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;
[0005] 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;
[0006] 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.
[0007] 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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Embodiment 1
[0044] Such as Figure 1~Figure 6 As shown, an aerothermal calculation method considering the surface mass ejection effect, including steps:
[0045] S1, obtaining the geometric shape of the hypersonic vehicle;
[0046] S2, meshing the acquired geometric shape of the hypersonic vehicle;
[0047] S3, acquire hypersonic incoming flow velocity data, hypersonic incoming flow temperature data, hypersonic incoming flow density data and hypersonic incoming flow pressure data, and input surface mass ejection gas mass flow rate data and surface mass ejection gas temperature data into the computer processor;
[0048] S4, in the computer processor, based on the data in step S3 and using the surface mass ejection gas constant data to calculate the surface mass ejection gas density data, the surface mass ejection gas velocity data, the surface mass ejection gas pressure data and the surface mass ejection gas data Mass ejection gas temperature data;
[0049] S5, in the computer processo...
Embodiment 2
[0051] On the basis of Embodiment 1, in step S2, the following sub-steps are included: for the combined working conditions of the hypersonic vehicle shape, the hypersonic vehicle is gradually drawn in the order of point-to-line, line-to-surface, and surface-to-body The mesh corresponding to the geometric shape, and then the meshing is completed.
Embodiment 3
[0053] On the basis of Embodiment 1, in step S4, include sub-steps:
[0054] S40, input surface mass injection gas mass flow rate , surface mass injection gas temperature and the surface mass ejection gas constant , and using the hypersonic incoming flow velocity data, hypersonic incoming flow temperature data, hypersonic incoming flow density data and hypersonic incoming flow pressure data obtained in step S3, the first layer of grid points adjacent to the wall is obtained by flow field calculation pressure , the density on the grid points of the first layer near the wall , the normal velocity on the grid point of the first layer near the wall ;
[0055] S41, calculate the surface mass injection gas density data according to the following formula :
[0056]
[0057] S42, using the surface quality ejection gas density data calculated in step S2 and the surface mass injection gas mass flow rate input in step S3 , according to the following formula to calcul...
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Abstract
The invention discloses an aerothermal calculation method considering surface mass ejection effects, comprising the steps of: S1, obtaining the geometric shape of a hypersonic vehicle; S2, performing grid division on the obtained geometric shape of the hypersonic vehicle; S3 , to obtain hypersonic incoming flow velocity data, hypersonic incoming flow temperature data, hypersonic incoming flow density data and hypersonic incoming flow pressure data, and input surface mass ejection gas mass flow rate data and surface mass ejection gas temperature data to In the computer processor; S4, calculate the surface mass ejected gas density data, the surface mass ejected gas velocity data, the surface mass ejected gas pressure data and the surface mass ejected gas temperature data; S5, calculate the hypersonic vehicle wall heat flow data, The aerodynamic thermal environment of the hypersonic vehicle is expressed through the wall heat flow data; the present invention can more accurately predict the aerodynamic thermal environment of the hypersonic vehicle including surface mass ejection.
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...
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