A Compressible Correction Method Based on Launder-sharma k-epsilon Model

A model, turbulence model technology, applied in the field of computational fluid dynamics Reynolds-average turbulent numerical simulation, can solve the problem of high heat flow prediction in the separation zone, and achieve the effect of suppressing the turbulent viscosity coefficient, maintaining robustness, and reducing wall heat flow

Active Publication Date: 2022-07-08
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Application Information

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Problems solved by technology

At present, high Mach number compressible turbulence has become an important research topic, and Reynolds-averaged turbulence model is mostly used for numerical simulation in engineering applications, among which the Lauder-Sharma k-epsilon model is mostly used in incompressible flow, for hypersonic There are still some limitations to the flow, e.g. over-predicted heat flow in the separation zone, etc.

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  • A Compressible Correction Method Based on Launder-sharma k-epsilon Model
  • A Compressible Correction Method Based on Launder-sharma k-epsilon Model
  • A Compressible Correction Method Based on Launder-sharma k-epsilon Model

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Embodiment 1

[0035] The invention discloses a compressible correction method based on the Launder-Sharma k-epsilon model. The Lauder-Sharma k-epsilon model:

[0036]

[0037]

[0038] where μ t =v t ρ, μ=νρ.

[0039] The viscosity coefficient in the prior art is:

[0040]

[0041] Among them, C ε1 ,C ε2 ,C μ ,σ ε , and σ k Represents a constant: C ε1 =1.44C ε2 =1.92C μ =0.09σ ε =1.3σ k =1;

[0042] Other,

[0043]

[0044]

[0045] where the turbulent Reynolds number R t =k 2 / (νε), the source term in the turbulence model equation is defined as:

[0046]

[0047]

[0048] A correction was added to the epsilon equation:

[0049]

[0050] where Y is the wall distance.

[0051] The method of the present invention constructs a compressible correction based on compressible flow characteristics, and defines the compressible correction as:

[0052]

[0053] Then, the viscosity coefficient formula is modified as:

[0054] Among them, the constant in...

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Abstract

The invention discloses a compressible correction method based on a Lauder-Sharma k-epsilon model, which belongs to the field of numerical simulation of Reynolds average turbulent flow in computational fluid mechanics. The method of the invention constructs a compressible correction based on the compressible flow characteristics, suppresses the excessively high turbulent viscosity coefficient in the separation zone, reduces the turbulent viscosity coefficient of the separation zone and reattachment, thereby effectively reducing the original Lauder‑Sharma k‑epsilon Model-predicted wall heat flow, while maintaining the original model's pre-separation zone properties and model robustness.

Description

technical field [0001] The invention belongs to the field of numerical simulation of Reynolds-averaged turbulent flow in computational fluid mechanics, in particular to a compressible correction method based on a Launder-Sharma k-epsilon model. Background technique [0002] Numerical simulation of turbulence has a wide range of application requirements in the process of hypersonic vehicle design and integrated design of propulsion systems. At present, high Mach number compressible turbulence has become an important research topic. In engineering applications, the Reynolds-averaged turbulence model is mostly used for numerical simulation. The Lauder-Sharma k-epsilon model is mostly used in incompressible flow. There are still some restrictions on the flow, such as over-prediction of heat flow in the separation zone, etc. SUMMARY OF THE INVENTION [0003] The purpose of the present invention is to provide a compressible correction method based on the Launder-Sharma k-epsilo...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F30/28G06F113/08G06F119/14
CPCG06F30/28G06F2113/08G06F2119/14Y02T90/00
Inventor 王新光毛枚良陈坚强陈琦万钊张毅峰江丁武何琨郭勇颜张子佩
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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