Unstructured boundary layer grid generation method based on grid framework

A grid generation and boundary layer technology, applied in the direction of instrumentation, design optimization/simulation, calculation, etc., can solve problems such as difficulty in background frame grid generation, avoid local and global crossing phenomena, and achieve grid accuracy and global consistency sex high effect

Active Publication Date: 2021-04-09
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Although this method has good efficiency and advantages in quality control and local modification of prism grids, it is difficult to generate background frame grids.

Method used

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  • Unstructured boundary layer grid generation method based on grid framework
  • Unstructured boundary layer grid generation method based on grid framework
  • Unstructured boundary layer grid generation method based on grid framework

Examples

Experimental program
Comparison scheme
Effect test

Embodiment

[0116] 1. Calculation examples and quality inspection

[0117] (1) the normal direction advances the boundary layer and contrasts with the method of the present invention

[0118] In order to verify the non-structural boundary layer grid generation technology based on the grid frame of the present invention, the normal advancing boundary layer is used to compare with the present invention, and the resulting grid is checked;

[0119] attached image 3 (Left) is the normal advancing method; attached image 3 (Right) is the grid method generated by the present invention. It can be seen from the figure that the overall quality of the grid is good, and when the number of normal advancing layers is high, normal vector collisions are likely to occur, but the present invention avoids this phenomenon;

[0120] (2) V-groove

[0121] The V-groove is the connection position between the fuselage and the wing in various aircrafts, and is a common structure. When the two planes are conn...

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PUM

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Abstract

The invention discloses an unstructured boundary layer grid generation method based on a grid framework, which comprises the following steps of: S1, performing digital-to-analog discretization by utilizing Pointwise to generate a surface grid which is used as input of the method; S2, extracting supporting points according to geometrical characteristics of the surface grid, and calculating a frame supporting line through the supporting points and normal vectors of the supporting points; S3, obtaining a contour line through a radial basis function interpolation method; S4, on the basis of the contour line and the surface grid, utilizing the radial basis function interpolation again to obtain a boundary layer top grid; and S5, generating an internal grid of the boundary layer through linear interpolation. It can be seen that the precision of the grid generated through the method meets the use requirement by conducting simulation experiments on the automation of generation and the control capacity of the quality of the local grid.

Description

technical field [0001] The invention belongs to the technical field of simulation grid generation, and in particular relates to a grid frame-based grid generation method for an unstructured boundary layer. Background technique [0002] The application of CFD (Computational Fluid Dynamics) in aerospace, automobile, high-speed rail and other fields is increasing day by day, and it has become an indispensable and important technical tool in many research fields. Through decades of development, the reliability of its calculation results has been recognized by the industry, which can be used as strong evidence for aerodynamic shape optimization. Among them, the grid generation in the pre-processing stage is an indispensable and important link in the CFD process, and it is the premise and basis for numerical calculation. The quality of grid generation directly affects the efficiency, accuracy and stability of numerical calculations. [0003] Among them, the boundary layer grid i...

Claims

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Application Information

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IPC IPC(8): G06F30/28G06F113/08G06F119/14
CPCG06F30/28G06F2113/08G06F2119/14
Inventor 刘杨庞宇飞齐龙谢冬香王硕何雨阳胡月凡陈波卢风顺
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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