A method for determining outer boundary of computational domain for numerical solution of steady flow around aircraft

A technology for numerical solution and determination method, applied in computing, instrumentation, electrical and digital data processing, etc., can solve the problems of computational grid waste, influence, and large selection of computational domain, so as to improve efficiency, reduce grid volume, and reduce Effects of Computational Fields

Active Publication Date: 2019-04-26
NAT UNIV OF DEFENSE TECH
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Problems solved by technology

[0004] In existing studies, the determination of the outer boundary of the calculation domain for the numerical solution of the steady flow around the aircraft mostly relies on experience. Streaming Numerical Solving Efficiency Brings Negative Impact

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  • A method for determining outer boundary of computational domain for numerical solution of steady flow around aircraft
  • A method for determining outer boundary of computational domain for numerical solution of steady flow around aircraft
  • A method for determining outer boundary of computational domain for numerical solution of steady flow around aircraft

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Embodiment Construction

[0037] The specific implementation manner of the present invention will be further described below in conjunction with the accompanying drawings. The process flow of the flow field initialization method for the numerical solution of the steady flow around the aircraft proposed by the present invention is as follows: figure 1 As shown, the method includes the following steps:

[0038] S1: Initially determine the outer boundary of the calculation domain and divide the grid:

[0039] Taking the standard model "AGARD HB-2" (Reference: Hypersonic Wind Tunnel Aerodynamic Test Method [Standard].GJB4399-2002.2002) as an example, its appearance is as follows: figure 2 shown. The input conditions for the numerical solution of the steady flow around it are: (1) the Mach number M of the incoming flow ∞ =7, pressure p ∞ =3000Pa, temperature T ∞ = 288.15K, angle of attack α = 10°, angle of sideslip β = 0° as an example; (2) The viscous model is the S-A model, and the wall boundary con...

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Abstract

The invention belongs to the technical field of computational fluid mechanics. The method discloses a determination method of the computational domain outer boundary for solving the steady circumfluence value of flying objects. The applied technical scheme includes the following steps: S1: determining the preliminary value of the outer boundary of the computational domain and conducting the mesh generation; S2: solving the flow field parameters of the steady circumfluence of the flying object in a simplified condition; S3: identifying the mesh points in the turbulent area of the steady circumfluence of the flying object in the simplified condition; S4: determining the computational domain outer boundary solved by incorporating the steady circumfluence value of the flying object. The method minimizes the computational domain to the largest extent, reduces the mesh quantity, upgrades the efficiency of the solving process of the steady circumfluence value of the flying objects; the flow field acquired in the simplified condition can be used as the initial flow field for solving subsequent flow fields and is beneficial to the modification of the stability and the convergence rate of the solving process of the subsequent flow fields. This method can be applied in all subsonic, transonic and supersonic incoming flows.

Description

technical field [0001] The invention belongs to the field of computational fluid dynamics, and in particular relates to a method for determining the outer boundary of a computational domain used for the numerical solution of a steady flow around an aircraft. Background technique [0002] Numerical solution of steady flow around aircraft is an important research direction in the field of computational fluid dynamics, and it is an important means to obtain flow characteristics and aerodynamic / thermal performance of aircraft. The basic steps of numerical solution for steady flow around aircraft are: (a) determination of computational domain of flow field; (b) grid division; (c) numerical solution; (d) data post-processing. The main task of determining the calculation domain of the flow field is to determine the outer boundary of the calculation domain. The determination of the calculation outer boundary directly determines the size of the solution domain, which in turn affects ...

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
CPCG06F30/15Y02T90/00
Inventor 彭科江振宇胡凡张为华张士峰向敏王东辉
Owner NAT UNIV OF DEFENSE TECH
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