Numerical simulation method for obtaining aircraft flow fields

A numerical simulation and aircraft technology, applied in the direction of instruments, electrical digital data processing, special data processing applications, etc., can solve problems such as difficult to give flow field structure, large numerical dissipation and numerical dispersion, so as to improve accuracy and reduce The effect of storage capacity and high-efficiency flow field display

Active Publication Date: 2017-05-17
CHINA ACAD OF AEROSPACE AERODYNAMICS
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Problems solved by technology

However, the existing flow field solver is based on the second-order precision calculation format. Although it has achieved great success in the numerical simulation of complex shape flow, the second-order precision calculation format has a large numerical dissipation and numerical Dispers

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  • Numerical simulation method for obtaining aircraft flow fields
  • Numerical simulation method for obtaining aircraft flow fields
  • Numerical simulation method for obtaining aircraft flow fields

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Embodiment Construction

[0036] The present invention obtains the numerical simulation method of aircraft flow field, adopts the discontinuous Galerkin method based on unstructured rectangular grid to solve flow field, and specific steps are as follows:

[0037] 1. Discretize the solution domain into a set of units by adopting a rectangular grid with a quadtree structure

[0038] First, according to the selected background grid and setting parameters, the initial grid is divided in the calculation domain, and then the cells near the object are encrypted with multi-layer quadtree, and then the grid cells inside the object and intersected with the object are deleted to generate a zigzag inner surface , the remaining grid is called the peripheral right-angle grid; then the inner surface is smoothed and projected to the object surface to generate a body-fitted viscous layer grid, and the body-fitted viscous layer grid (parent grid) is divided to generate layers Sub-grids with the same number and spacing, ...

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Abstract

The invention relates to a numerical simulation method for obtaining aircraft flow fields, wherein an interrupted Galerkin method based on non-structural right angle meshes is used to solve the flow field, and right angle meshes with a quadtree structure are used to disperse a to-be-solved flow field area into a set of meshes; each quadrilateral mesh is processed by dual-linear coordinate conversion, so each mesh under a current physical coordinate system can be mapped onto the next regular mesh in a computational coordinate system, so standard square meshes can be obtained; conservation variables in units under the computational coordinate system are obtained through numerical computation; a front face, a lower face, a left face and a right face of each mesh under the physical coordinate system are determined; according to differences between the left and right vibrations of unit interfaces, an interrupted detector is established; and the conservation variables in each mesh are processed by flow field display on the disperse meshes, so flow field distribution can be obtained. According to the invention, the interrupted Galerkin method based on the non-structural right angle meshes is introduced into flow field computation, so accuracy of the flow field computation is increased, and complicated flow phenomena can be solved.

Description

technical field [0001] The invention relates to a numerical simulation method for obtaining the flow field of an aircraft, belonging to the field of computational fluid dynamics. Background technique [0002] The structure of computational fluid dynamics software generally consists of three parts: pre-processing, solver and post-processing. Pre-processing mainly includes geometric model construction and grid division; solver includes discretization of control equations and selection of numerical calculation methods; post-processing includes Computer visualization and animation processing of velocity field, temperature field, pressure field and other flow field parameters. [0003] Compared with the traditional structured grid discretization method, the superior geometric flexibility of the unstructured rectangular grid can adapt to any complex shape, and its random data structure is very conducive to grid adaptation. However, the existing flow field solver is based on the s...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/23Y02T90/00
Inventor 刘帅何跃龙李盾
Owner CHINA ACAD OF AEROSPACE AERODYNAMICS
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