简化三方程转捩模型在高超声速流动中的应用

蔡林峰; 李昊歌; 赵文文; 陈伟芳

doi:10.7638/kqdlxxb-2017.0172

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简化三方程转捩模型在高超声速流动中的应用

研究论文 | 更新时间：2026-05-28

- 简化三方程转捩模型在高超声速流动中的应用
- Application of simplified three-equation transition model in hypersonic flow
- 空气动力学学报 2019年37卷第6期页码：945-949
- 作者机构：
  
  浙江大学航空航天学院,浙江,杭州,310027
- 作者简介：
  
  蔡林峰(1992-), 男, 浙江湖州人, 硕士研究生, 主要从事湍流转捩研究.E-mail:linfengcai@zju.edu.cn
  陈伟芳(1970-), 男, 湖南隆回人, 博士, 教授, 主要从事高超声速空气动力学研究.E-mail:chenwfnudt@163.com
- 基金信息：
  
  国家自然科学基金（11572284，51575487）;国家自然科学基金青年基金（11502232）
- DOI：10.7638/kqdlxxb-2017.0172
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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蔡林峰, 李昊歌, 赵文文, 陈伟芳. 简化三方程转捩模型在高超声速流动中的应用[J]. 空气动力学学报, 2019, 37(6): 945-949.

CAI Linfeng, LI Haoge, ZHAO Wenwen, et al. Application of simplified three-equation transition model in hypersonic flow[J]. 2019, 37(6): 945-949.
蔡林峰, 李昊歌, 赵文文, 陈伟芳. 简化三方程转捩模型在高超声速流动中的应用[J]. 空气动力学学报, 2019, 37(6): 945-949. DOI： 10.7638/kqdlxxb-2017.0172.

CAI Linfeng, LI Haoge, ZHAO Wenwen, et al. Application of simplified three-equation transition model in hypersonic flow[J]. 2019, 37(6): 945-949. DOI： 10.7638/kqdlxxb-2017.0172.

摘要

在雷诺平均方法的基础上，通过耦合

k-ω

SST湍流模型和间歇因子转捩模型，引入湍流模型和转捩模型的可压缩修正方法，对高超声速平板、双楔、尖锥三类模型边界层转捩流动开展了数值模拟研究。与实验结果的对比分析表明基于压力梯度表征参数

Ω/ω

的简化三方程转捩模型，能够准确捕捉高超声速平板边界层流动的转捩起始位置、转捩区域长度以及湍流区壁面热流。而对于双楔、尖锥模型，改进前的简化三方程转捩模型由于受到流动可压缩效应的影响，边界层转捩后湍流区的壁面热流模拟预测结果明显高于实验值。在添加模型可压缩修正方法后，转捩区域长度和湍流区壁面热流模拟结果得到有效改善，与实验值吻合较好。可见，简化三方程转捩模型在添加可压缩修正方法后具备准确模拟预测高超声速边界层流动转捩的潜力。

Abstract

On the basis of the RANS model

the numerical simulation study of hypersonic boundary-layer transitional flow was carried out on a flat-plate

a double wedge

and a cone by modifying

k-ω

SST turbulence model and the intermittency transition model with compressibility correction. Based on the comparison with experimental result

it is shown that the simplified three-equation transition model based on the pressure gradient characterization parameter

Ω/ω

can correctly catch the transition onset location

the length of transition region

and the turbulent z

one heat flux on the wall for the flat-plate hypersonic boundary-layer flow. For the double wedge and cone case

the wall heat flux in turbulent zone calculated by the simplified three-equation transition model is much higher than the experimental data due to the flow compression effects. However

it can agree well with the experimental data after adding compressibility correction to the model. The simplified three-equation transition model with appropriate compressibility correction has potential to simulate hypersonic boundary-layer transitional flow correctly.

关键词

Keywords

references

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