A Multi-Grid Perturbation Domain Update Acceleration Method for Numerical Simulation of Flow Around Aircraft

A numerical simulation, multi-grid technology, applied in special data processing applications, geometric CAD, design optimization/simulation, etc., can solve problems such as invalid calculation, and achieve the effect of reducing storage space requirements and improving computing efficiency

Active Publication Date: 2022-04-08
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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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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  • A Multi-Grid Perturbation Domain Update Acceleration Method for Numerical Simulation of Flow Around Aircraft
  • A Multi-Grid Perturbation Domain Update Acceleration Method for Numerical Simulation of Flow Around Aircraft
  • A Multi-Grid Perturbation Domain Update Acceleration Method for Numerical Simulation of Flow Around Aircraft

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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 perturbation domain update acceleration method for the numerical simulation of the flow around the aircraft. Aiming at the problem of a large number of invalid calculations in the existing multi-grid method when simulating the flow around the aircraft, the fine grid and the coarse grid The convective and viscous dynamic calculation domains are used above, so that the flow control equations are solved in the convective dynamic calculation domain that only contains unconverged disturbed units in each iteration step, and the viscous effect is only in the viscous dominant unit. Considered in the viscous dynamic calculation domain, the solution idea of ​​only solving the unconverged disturbed elements and only considering the viscous effect in the local area is realized. By effectively reducing the calculation amount of a single iteration step and the number of iteration steps required to reach the convergence state, the invention can significantly improve the calculation efficiency of the multi-grid method for simulating the flow around the aircraft.

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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Patent Type & Authority Patents(China)
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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