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A hypersonic transition prediction method based on a simplified three-equation transition model

A hypersonic, predictive method technology, applied in design optimization/simulation, instrumentation, calculation, etc., to achieve the effect of reducing the amount of calculation

Active Publication Date: 2018-12-18
ZHEJIANG UNIV
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Problems solved by technology

However, this method cannot be directly used for numerical simulation and prediction of hypersonic boundary layer flow transitions.

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  • A hypersonic transition prediction method based on a simplified three-equation transition model
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  • A hypersonic transition prediction method based on a simplified three-equation transition model

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Embodiment Construction

[0043] The specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings, and the purpose and effects of the present invention will become more apparent.

[0044] The core content of a hypersonic transition prediction method based on a simplified three-equation transition model is to construct a new transition empirical determination relationship by introducing localized pressure gradient characterization parameter fitting, thereby removing the transition momentum thickness Reynolds number output This equation is then coupled with the compressible correction method of the turbulence / transition model to simulate the transition of the hypersonic boundary layer flow. The main construction process of the present invention is detailed in figure 1 . Specific steps are as follows:

[0045] Step (1) Use the conventional finite volume method to solve the NS equation, k-w SST turbulence model equation, and intermittent factor tra...

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Abstract

The invention discloses a hypersonic transition prediction method based on a simplified three-equation transition model. On the basis of a gamma-Re theta t transition model, a new empirical transitionrelation is constructed by introducing the localized pressure gradient parameter, and the transport equation of transition momentum thickness Reynolds number Re theta t is successfully eliminated. Onthis basis, the simulation and prediction of hypersonic boundary layer flow transition are realized by the coupled turbulence / transition model compressible correction method. Compared with the gamma-Re theta t transition model, the hypersonic transition prediction method has a simpler empirical transition relation, and the computational complexity decreases. The hypersonic transition prediction method can accurately predict the onset of hypersonic boundary layer transition, the length of transition region, and the heat flux and friction coefficient on the surface of the hypersonic body.

Description

Technical field [0001] The invention relates to a numerical calculation method for boundary layer flow transition, in particular to a hypersonic transition prediction method based on a simplified three-equation transition model. Background technique [0002] The study of boundary layer transition not only helps to reveal complex turbulence formation mechanisms, but also effectively guides engineering design in the aerospace field. As early as 1992, the Defense Science Committee of the US Department of Defense considered that the simulation and prediction of boundary layer transition was one of the key technologies in its national aerospace aircraft project. One of the three hypersonic vehicle research centers established by NASA in March 2009 is the "National Hypersonic Laminar Flow / Turbulent Transition Research Center." It was also mentioned in the "CFD Vision 2030" published by NASA in 2014: The description of the physical model of turbulence / transition flow is the first type ...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/23Y02T90/00
Inventor 陈伟芳吴昌聚赵文文杨华陈丽华蔡林峰刘华林
Owner ZHEJIANG UNIV
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