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Post-processing method for automatic partition of aerodynamic flow field grid by Metis

A technology of automatic partitioning and gridding, applied in electrical digital data processing, special data processing applications, instruments, etc., can solve the problems of undisclosed aerodynamic flow field grids, post-division processing methods, etc.

Active Publication Date: 2016-05-04
BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST +1
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Problems solved by technology

However, for the output data divided by METISmpmetis, due to the difference in problem types, there is currently no post-processing method for aerodynamic flow field grid division.

Method used

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  • Post-processing method for automatic partition of aerodynamic flow field grid by Metis
  • Post-processing method for automatic partition of aerodynamic flow field grid by Metis
  • Post-processing method for automatic partition of aerodynamic flow field grid by Metis

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Embodiment Construction

[0061] The technical solutions of the present invention will be further described below in conjunction with the accompanying drawings and specific embodiments.

[0062] figure 1 It is an aerodynamic flow field containing 1-6 grid units, where edges are adjacent surfaces and circles are grid units, which are divided into 3 partitions, numbered 0, 1, and 2 respectively. The data format of the grid unit part after Metis automatic partition (named Metis unit data) is as follows figure 2 As shown, it only indicates the partition to which each grid cell belongs. The grid point data format is similar.

[0063] A kind of post-processing method of Metis automatic partition of aerodynamic flow field grid of the present invention comprises the following steps:

[0064] Set the grid A of the aerodynamic flow field to be partitioned to include M grid points, N grid units, and the number of partitions to be P; Metis automatically generates the data of the partition to which the N grid u...

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Abstract

The invention belongs to the technical field of the data post-processing method, specifically relates to a post-processing method for automatic partition of an aerodynamic flow field grid by Metis. The method comprises following steps: step 1, deleting redundant grid point data; step 2, generating an undirected graph TA of an aerodynamic flow field grid A according to a following method; step 3, creating an array E[4][N]; step 4, determining the boundary elements of the grid A according to the undirected graph TA and a following boundary element judging method, and the like, finally outputting grid point sets G1, G2, and the like, GP of each subarea, wherein the grid element sets of each subarea respectively are E1, E1, and the like, EP, the inner boundary sets are B1, B2, and the like, BP; and finishing post-processing. According to the method, the renumbering demands of the grid elements and grid points in each subarea can be satisfied; and the boundary elements of the inner boundaries of the grids of each subarea can be determined rapidly.

Description

technical field [0001] The invention belongs to the technical field of data post-processing methods, and in particular relates to a post-processing method for Metis automatic partitioning of aerodynamic flow field grids. Background technique [0002] CFD (Computational Fluid Dynamics) is a discipline that obtains flow data under various conditions and forces, moments, flow images and heat acting on objects that flow around them by numerically solving the basic equations of fluid and gas dynamics on a computer. It plays an important role in the aerodynamic shape design and optimization of similar aviation and aerospace vehicles. CFD calculations are generally carried out in an iterative manner, and thousands to tens of thousands of iterations are required to reach the convergence condition, so parallel computing technology is needed to speed up the calculation. [0003] With the continuous advancement of parallel numerical calculation methods and the rapid development of hig...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
Inventor 龚春叶陈政王玲高鹏张星郭灵犀禹彩辉方洪郑昭虎
Owner BEIJING LINJIN SPACE AIRCRAFT SYST ENG INST
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