Improved hot wall correction method considering hypersonic chemical non-equilibrium effect

A hypersonic, non-equilibrium technology, used in chemical process analysis/design, design optimization/simulation, special data processing applications, etc., can solve the problem of not considering the influence of chemical non-equilibrium effects, and achieve high computational efficiency.

Pending Publication Date: 2020-10-30
AERODYNAMICS NAT KEY LAB
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Problems solved by technology

[0003] The above-mentioned conventional hot wall correction method is developed for calorimetric complete gas, and does not consider the influence of the chemical n

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  • Improved hot wall correction method considering hypersonic chemical non-equilibrium effect
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  • Improved hot wall correction method considering hypersonic chemical non-equilibrium effect

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Embodiment Construction

[0029] The present invention will be further described below in conjunction with the accompanying drawings.

[0030] The present invention provides an improved thermal wall correction method considering hypersonic chemical non-equilibrium effects, which is applicable to physical problems such as figure 1 shown.

[0031] The improved hot wall correction method of the present invention is developed based on the influence law of high temperature chemical effects of the wall surface on the heat flow of the wall surface and the linearity of the wall surface temperature. The study on the chemical non-equilibrium effect shows that although the linearity between the convective heat flow caused by reaction diffusion and the wall temperature becomes worse, the convective heat flow caused by the temperature gradient and the wall temperature still maintain a high linearity. Therefore, the convective heat flow can be decomposed according to the contribution of the physical process. The he...

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Abstract

The invention relates to the technical field of hot wall correction methods and discloses an improved hot wall correction method considering a hypersonic chemical unbalance effect for aerodynamic heating numerical prediction of a high-speed aircraft. According to the method, convection heat flow is decomposed according to contribution of a physical process, a heat flow part caused by temperature gradient meets a traditional linear hot wall correction method, a heat flow part caused by reaction diffusion is related to wall surface high-temperature chemical action, and corresponding treatment iscarried out according to a wall surface chemical reaction mechanism. Respectively solving the heat flow caused by the temperature gradient and the heat flow caused by the reaction diffusion, and adding the solved heat flows to obtain the total heat flow of the wall surface. According to the method provided by the invention, only the hypersonic flow field under the conditions of the cold wall andthe heat insulation wall needs to be solved, fluid-solid coupling iterative solution is not needed, and the calculation efficiency is high.

Description

technical field [0001] The invention relates to the technical field of hot wall correction methods, in particular to an improved hot wall correction method considering hypersonic chemical non-equilibrium effects. Background technique [0002] When using computational fluid dynamics technology to predict the aerodynamic heating characteristics of hypersonic speeds, it is necessary to solve the aerodynamic thermal loads on the aircraft under different wall thermal states and coupling conditions with the heat-resistant structure, which will consume huge computing costs and computer resources, and affect the aerodynamic design of the aircraft cycle. For the same incoming flow and layout conditions, considering that the wall heat flow and temperature approximately satisfy a linear relationship within a certain temperature range of concern, that is, the Stanton number describing the convective heat transfer coefficient is a constant value, and the current engineering design usuall...

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Application Information

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IPC IPC(8): G06F30/15G06F30/28G16C20/10G06F111/10G06F113/08G06F119/08G06F119/14
CPCG06F30/15G06F30/28G16C20/10G06F2111/10G06F2113/08G06F2119/08G06F2119/14Y02T90/00
Inventor 杨肖峰肖光明刘磊曾磊魏东杜雁霞桂业伟向静
Owner AERODYNAMICS NAT KEY LAB
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