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

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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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 non-equilibrium effect after the shock wave induced by the hypersonic flow, and needs to be improved for the physical mechanism of the chemical non-equilibrium effect

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