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Numerical calculation method and device for flow field data under thermochemical unbalanced condition

A thermochemical, non-equilibrium technology, applied in the direction of complex mathematical operations, electrical digital data processing, CAD numerical modeling, etc., to achieve the effect of reliable acquisition

Pending Publication Date: 2020-06-02
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0005] Based on this, it is necessary to provide a numerical calculation method and device for flow field data under thermochemical non-equilibrium conditions to solve the technical problem that the traditional shock wave capture method cannot accurately and reliably obtain flow field data under non-equilibrium conditions

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  • Numerical calculation method and device for flow field data under thermochemical unbalanced condition
  • Numerical calculation method and device for flow field data under thermochemical unbalanced condition

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[0045] In order to make the purpose, technical solution and advantages of the present application clearer, the present application will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present application, and are not intended to limit the present application.

[0046]In one embodiment, such as figure 1 As shown, a numerical calculation method for flow field data under thermochemical non-equilibrium conditions is provided, and the application of this method to the terminal is taken as an example to illustrate, including the following steps:

[0047] Step 102, selecting a chemical reaction model.

[0048] The gas in the chemical reaction model includes various components in the air, such as: N2, O2, NO, N and O, etc. By selecting the chemical reaction model, the reaction conditions that occur in the air under the thermochemical no...

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Abstract

The invention relates to a numerical calculation method and device for flow field data under a thermochemical unbalanced condition. The method comprises the steps that a chemical reaction model is selected, and gas in the chemical reaction model comprises all components in air; depending on a chemical reaction model, constructing a thermochemical non-equilibrium control equation based on a Navid-Stokes equation; discretizing the thermochemical equilibrium control equation according to pre-acquired grid data; selecting pressure values of grid nodes in advance according to the grid data, constructing a pressure correction item, correcting the thermochemical non-equilibrium flux format according to the pressure correction item to obtain a pressure correction thermochemical non-equilibrium flux format, and iteratively solving the discrete control equation according to the pressure correction thermochemical non-equilibrium flux format to obtain flow field simulation data in the flow area. By adopting the method, the flow field simulation data can be accurately and reliably obtained in the thermochemical non-equilibrium fluid.

Description

technical field [0001] The present application relates to the technical field of computational fluid dynamics, in particular to a numerical calculation method and device for flow field data under thermochemical non-equilibrium conditions. Background technique [0002] The calorimetric complete gas assumption is widely used in the study of aerodynamics. In this assumption, only the translational energy and rotational energy in the gas are fully excited, and the two can quickly reach equilibrium. The internal energy of the gas is linear with the temperature. relation. When the aircraft is flying at hypersonic speed, a strong bow shock wave will be formed in front of the blunt body. When the gas passes through the shock wave, it will be heated to a very high temperature. As the temperature rises, the vibrations in the gas molecules Energy and electronic energy are excited, and the time for vibrational energy and electronic potential energy to reach equilibrium is much longer t...

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Application Information

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IPC IPC(8): G06F30/20G06F119/14G06F111/10G06F17/11
CPCG06F17/11
Inventor 李桦于航田正雨谢文佳赖剑奇张烨杨帆
Owner NAT UNIV OF DEFENSE TECH
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