Numerical simulation method for obtaining aircraft flow fields

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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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 Dispersion, for some complex flow phenomena, such as separation flow, aerodynamic noise, turbulent flow, etc., it is still difficult to give a fine flow field structure, especially for large eddy simulation and direct numerical simulation of turbulent flow, high-order precision schemes must be used

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