γ-Reθ转捩模型在高超声速下的应用及分析

推进技术 ›› 2014, Vol. 35 ›› Issue (3): 296-304.

γ-Reθ转捩模型在高超声速下的应用及分析

郑赟,李虹杨,刘大响

北京航空航天大学能源与动力工程学院,北京 100191;北京航空航天大学能源与动力工程学院,北京 100191;北京航空航天大学能源与动力工程学院,北京 100191

发布日期:2021-08-15
作者简介:郑赟(1971—),男,博士,讲师,研究领域为计算流体力学,叶轮机流、热、固耦合仿真,航空发动机叶片振动数值仿真。E-mail:zheng_yun@buaa.edu.cn 通讯作者:李虹杨(1989—),男,博士生,研究领域为高超声速流动数值仿真,流、热耦合仿真。E-mail:lihongyang1989@yahoo.com.cn

Application and Analysis of γ-Reθ Transition Model in Hypersonic Flow

School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China;School of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China

Published:2021-08-15

摘要/Abstract

摘要： 为了初步研究γ-Reθ转捩模型在高超声速领域的适用性,在自行开发的CFD程序中添加了该模型,利用T3系列平板算例对该模型的实现进行了验证；针对高超声速流动,选取压缩面绕流和双圆锥扰流等算例,分别利用该转捩模型、全层流模拟、以及传统的湍流模型进行了数值模拟计算,并与实验结果进行对比。计算结果表明,尽管该转捩模型是在低速流动的基础上发展的,它仍能准确预测高超声速流动下的转捩现象。 

关键词: 转捩模型;间歇因子;湍流模型;高超声速流动 

Abstract: The feasibility of γ-Reθ transition model on hypersonic flows was studied by an in-house CFD software. The model was verified by turbulent flows over the T3flat plate for low speed flows. Numerical simulations were conducted for hypersonic flows,taking the around compressible corners and double cone with laminar flow as the examples, with traditional turbulence models and also transition model in order to assess the capability of these models for high speed flows. The computed surface pressure and heat transfer rate were compared with the experimental data. The results indicate that although this transition model is correlated for low speed flows, it could be used to predict the flow transition for hypersonic flows .

Key words: Transition model; Intermittency factor; Turbulence model; Hypersonic flow

郑赟,李虹杨,刘大响. γ-Reθ转捩模型在高超声速下的应用及分析[J]. 推进技术, 2014, 35(3): 296-304.

ZHENG Yun, LI Hong-yang, LIU Da-xiang. Application and Analysis of γ-Reθ Transition Model in Hypersonic Flow[J]. Journal of Propulsion Technology, 2014, 35(3): 296-304.

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