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Blunt body flow field shock wave self-adaptive structure grid generation method

A grid generation, blunt body technology, applied in the field of computational fluid dynamics grid generation, blunt body flow field shock wave adaptive structural grid generation, can solve the problem of low accuracy, reduce numerical calculation errors, ensure Effects of matching characteristics and improving simulation accuracy

Active Publication Date: 2020-01-14
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

[0003] Most of the current flow field adaptive technologies are based on unstructured grids. However, the accuracy of aerothermal calculations using unstructured grids is low. In engineering applications, aerothermal calculations mainly rely on structured grids, and there is currently no standard structure. Grid Shock Wave Adaptive Generation Method to Solve Such Problems

Method used

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  • Blunt body flow field shock wave self-adaptive structure grid generation method
  • Blunt body flow field shock wave self-adaptive structure grid generation method
  • Blunt body flow field shock wave self-adaptive structure grid generation method

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Embodiment Construction

[0040] The blunt body is any shape that can generate a completely detached shock wave. It does not need to ensure surface symmetry or axis symmetry. It is suitable for working conditions where the incoming flow has an angle of attack and a sideslip angle.

[0041] Calculate the initial three-dimensional full flow field data according to the incoming flow conditions in front combined with the initial flow field grid; capture the shock wave grid points according to the flow field Mach number distribution, assemble the shock wave grid points into a shock wave grid surface and The grid surface is smoothed; the flow field grid is reconstructed with the shock wave grid surface as the internal docking boundary so that the grid near the shock wave is distributed along the shock wave surface and the grid is refined in the direction perpendicular to the shock wave. The reconstructed flow field grid recalculates the three-dimensional full flow field data; iterative flow field calculation,...

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Abstract

The invention discloses a blunt body flow field shock wave self-adaptive structure grid generation method. A blunt body flow field is a flow field in which a blunt body moves at a high speed in air and can generate complete separation shock waves in front of the blunt body, and the blunt body flow field self-adaptive structure grid generation method is achieved through the following steps: calculating initial three-dimensional full flow field data according to front incoming flow conditions in combination with initial flow field grids; capturing shock wave grid points according to the Mach number distribution of the flow field, assembling the shock wave grid points into a shock wave grid surface, and carrying out fairing processing on the shock wave grid surface; reconstructing a flow field grid by taking the shock wave grid surface as an internal butt joint boundary, so as to enable grids near the shock wave to distributed along the shock wave surface and encrypting the grids in a direction perpendicular to the shock wave, and recalculating three-dimensional full-flow-field data by adopting the reconstructed flow field grid; carrying out iterative flow field calculation, shock wave capture and grid reconstruction automatically until the error between the two shock wave grid surfaces is smaller than a preset threshold value, and completing shock wave adaptive generation of thestructural grid, wherein the flow field grid is a multi-region butt joint structured hexahedral grid.

Description

technical field [0001] The invention relates to a calculation fluid dynamics grid generation method, in particular to a blunt body flow field shock wave self-adaptive structural grid generation method, which belongs to the technical field of flow field numerical simulation and grid generation. Background technique [0002] The blunt body is a typical shape of an aircraft. When the blunt body aircraft reaches a certain flight speed in the air, the airflow is strongly compressed in front of the blunt body and generates a strong shock wave. The kinetic energy is dissipated in the boundary layer due to the gas viscosity and converted into internal energy, and part of the energy is transferred to the blunt body through aerodynamic heating. The temperature of the heat-resistant material gradually increases, resulting in a decrease in the strength and stiffness of the heat-resistant material. It may even be burned, which will affect the safe flight of the aircraft. Therefore, it is...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/23
CPCY02T90/00
Inventor 施家桐张亮陈智林博希郝景科史可天张学军李俊红江娟张青青
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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