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Multi-resolution WENO format and ILW boundary processing combined fixed-point rapid scanning method

A multi-resolution, boundary processing technology, used in electrical digital data processing, special data processing applications, instruments, etc.

Pending Publication Date: 2021-02-02
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0008] A multi-resolution WENO format combined with ILW boundary processing fixed-point rapid scanning method, characterized in that the method is used for high-precision numerical simulation of compressible steady flow field problems in various complex calculation areas, including:

Method used

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  • Multi-resolution WENO format and ILW boundary processing combined fixed-point rapid scanning method
  • Multi-resolution WENO format and ILW boundary processing combined fixed-point rapid scanning method
  • Multi-resolution WENO format and ILW boundary processing combined fixed-point rapid scanning method

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Embodiment 1

[0220] Embodiment 1. Classical normal shock wave reflection calculation example. The lower boundary is the reflective boundary, the left and upper boundaries are the Dirichlet boundary, and the right boundary is the supersonic exit. The calculation area is [0,4]×[0,1]. The numerical results are as follows figure 1 shown.

Embodiment 2

[0221] Embodiment 2. Calculation example of flow around a supersonic cylinder. The calculation area is [-0.5,0]×[-0.5,0.5], the radius of the cylinder is 0.05, the center of the circle is at the origin, and the inflow velocity is Mach 3. The numerical results are as follows figure 2 shown.

Embodiment 3

[0222] Embodiment 3. Calculation example of flow around a supersonic NACA0012 airfoil. The calculation area is [-1.5,1.5]×[-1.5,1.5], the inflow velocity is Mach 2, and the impact angle is 1 degree. Its numerical result is as image 3 shown.

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Abstract

The invention discloses a multi-resolution WENO format and ILW boundary processing combined fixed-point rapid scanning method, and the method comprises the following steps: converting a steady hyperbolic conservation law problem into a time-dependent hyperbolic conservation law problem, and processing an object surface boundary by using a novel five-order ILW boundary processing method; discretizing a space part of the hyperbolic conservation law equation by using a finite difference multiple resolution weighting basic oscillation-free format; discretizing a time part in the control equation by using a three-order Runge-Kutta method and a fixed-point rapid scanning method; obtaining an approximate value of each point of the next time layer according to a space-time full-discrete method, and obtaining a numerical simulation result when the residual error of the conservation variable in the calculation region tends to be stable. According to the method, the advantage that the high-orderprecision of the calculation format near the boundary of the object plane is not reduced can be kept, the use number of space templates is effectively reduced, parameters needing to be manually adjusted are reduced, implementation is simpler, and implementation is easy.

Description

technical field [0001] The invention belongs to the technical field of computational fluid dynamics engineering, and in particular relates to a fixed-point rapid scanning method in combination with multi-resolution WENO format and ILW boundary processing. Background technique [0002] The steady-state problem of the hyperbolic conservation law equation is a mathematical problem often encountered in the field of fluid mechanics, and it also occupies an important position in engineering applications. Therefore, it is very important to construct a highly robust and high-precision numerical simulation method to solve such problems, and many scholars have also overcome difficulties in this field. Due to the variety of calculation areas in the actual problem, it is difficult for the residual of the physical quantity to converge to machine zero. Therefore, it is extremely important to design a high-precision algorithm that can reduce the residual error to the object plane boundary...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/28G06F30/23G06F111/10G06F113/08G06F119/14
CPCG06F30/28G06F30/23G06F2111/10G06F2113/08G06F2119/14
Inventor 李良朱君
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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