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Multi-grid disturbance domain updating acceleration method for aircraft streaming numerical simulation

A multi-grid and numerical simulation technology, applied in special data processing applications, geometric CAD, sustainable transportation, etc., can solve problems such as invalid calculations

Active Publication Date: 2020-10-30
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] In view of this, the present invention provides a multi-grid perturbation domain update acceleration method for numerical simulation of the flow around the aircraft to solve the problem of a large number of invalid calculations in the current multi-grid method when simulating the flow around the aircraft

Method used

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  • Multi-grid disturbance domain updating acceleration method for aircraft streaming numerical simulation
  • Multi-grid disturbance domain updating acceleration method for aircraft streaming numerical simulation
  • Multi-grid disturbance domain updating acceleration method for aircraft streaming numerical simulation

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Embodiment 1

[0117] Embodiment 1: as figure 1 As shown, the above-mentioned multi-grid disturbance domain update acceleration method provided by the present invention specifically includes the following steps:

[0118] The first step: data read in.

[0119] The read-in data includes the fine mesh of the aircraft flow field, preset calculation domains, boundary conditions and calculation settings.

[0120] Step 2: Generate a coarse mesh.

[0121] Generate a coarse grid with a specified number of layers by sparse fine grid. For structured grids, the commonly used coarse grid generation method is to double the fine grid along all grid directions, figure 2 The coarse grid generation method is illustrated by taking one-dimensional as an example. figure 2 Among them, h represents the fine grid, 2h and 4h represent the coarse grid of the first layer and the second layer respectively. That is, each unit of the coarse grid of the first layer contains 2 fine grid units, and each unit of the c...

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Abstract

The invention discloses a multi-grid disturbance domain updating acceleration method for aircraft streaming numerical simulation. Aiming at the problem that a large number of invalid calculations exist when an existing multi-grid method simulates aircraft streaming, two dynamic computational domains of convection and viscosity are adopted on a fine grid and a coarse grid, thus solving the flow control equation in each iterative step in a convection dynamic calculation domain only containing non-convergent disturbed units; and the viscous effect is only considered in the viscous dynamic calculation domain only containing the viscous effect leading unit, so that the solving thought of only solving the non-convergent disturbed unit and only considering the viscous effect in the local area isrealized. By effectively reducing the calculation amount of a single iterative step and the number of iterative steps required for achieving a convergence state, the calculation efficiency of simulating the aircraft streaming by the multi-grid method can be remarkably improved.

Description

technical field [0001] The invention relates to the technical field of computational fluid dynamics, in particular to a multi-grid disturbance domain update acceleration method for numerical simulation of flow around an aircraft. Background technique [0002] With the rapid development of computer technology, computational fluid dynamics numerical simulation has become one of the important technical supports for the aerodynamic design of contemporary aircraft. Although numerical simulation can accurately predict the static and dynamic aerodynamic characteristics of aircraft, for aircraft aerodynamic design, there is still a problem that the calculation efficiency of numerical simulation is difficult to meet the growing practical application requirements. Therefore, it is of great significance and engineering application value to propose an efficient method suitable for numerical simulation of flow around aircraft to improve the iteration efficiency of aircraft design and sho...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/28
CPCG06F30/15G06F30/28Y02T90/00
Inventor 蒋崇文胡姝瑶高振勋李椿萱
Owner BEIHANG UNIV
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