CKDO一方程模型计算高超声速横流转捩

王浩; 徐晶磊

doi:10.7638/kqdlxxb-2021.0296

CKDO一方程模型计算高超声速横流转捩

doi: 10.7638/kqdlxxb-2021.0296

王浩^{1, 2,},
徐晶磊^{1, 3, ,}

1.
北京航空航天大学能源与动力工程学院，北京　100191
2.
上海交通大学航空航天学院，上海　200240
3.
北京航空航天大学杭州创新研究院（余杭）航空学院，杭州　310023

基金项目: 国家数值风洞工程（NNW2019ZT3-A14）

详细信息

作者简介:
王浩（1995-），男，安徽人，博士研究生，研究方向：湍流模型，流转捩. E-mail：zy1704317@buaa.edu.cn

通讯作者:
徐晶磊^*，副研究员，研究方向：湍流模型，转捩模型，气动热，涡流减阻. E-mail：xujl@buaa.edu.cn

中图分类号: O357.4⁺1
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- 被引次数: 0
出版历程
- 收稿日期: 2021-09-29
- 录用日期: 2021-11-25
- 修回日期: 2021-11-01
- 网络出版日期: 2022-01-10
- 刊出日期: 2023-02-25

CKDO one-equation RANS simulation on transition of hypersonic cross flow

WANG Hao^{1, 2
,},
XU Jinglei^{1, 3
, ,}

1.
School of Energy and Power Engineering, Beihang University, Beijing　100191, China
2.
School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai　200240，China
3.
School of Aviation, Hangzhou Innovation Institute (Yuhang), Beihang University, Hangzhou　310023, China

摘要

摘要: 高超声速横流转捩集湍流-激波作用、可压缩、横流、转捩等难题于一身，基于雷诺平均N-S方程（RANS）的转捩建模是一项挑战。本文采用CKDO-tran计算高超声速横流转捩的经典标模—HIFiRE-5，分可压缩性效应、雷诺数效应和迎角效应进行评估，发现：不考虑可压缩效应的KDO-tran模型无法给出准确的预测，而不引入特定转捩机理，CKDO-tran仍然可以预测一系列雷诺数工况的高超声速横流转捩。迎角0°时，CKDO-tran可以较好地预测出双肺叶转捩图像，迎角为4°时，CKDO-tran产生的转捩线提前，但给出了与实验相似的转捩图像，具有进一步开发的潜力。对4°工况进行来流湍流度敏感性的研究发现，随着来流湍流度减小，CKDO-tran产生的转捩线逐渐后移，并且转捩图像与实验的相似性逐渐减弱直至消失。通过对迎角效应进行的分析，推测出来流-激波相互作用的建模是消除迎角效应的关键。
- 转捩模型 /
- 湍流模型 /
- 横流转捩 /
- 高超声速 /
- 可压缩效应
Abstract: Hypersonic cross-flow transition problem contains turbulence-shock effects, compressibility, cross-flow, transition, and many other phenomenons. This work employs the CKDO-tran model to simulate HIFiRE-5 which is a canonical model for hypersonic cross-flow transition. The compressibility effect, Reynolds number effectand attack angle effectare studied. It is found that the KDO-tran model without considering the compressibility effect cannot give an accurate prediction on transition, while it can predict the hypersonic cross-flow transition at different Reynolds number conditions, without introducing a specific transition mechanism. When the angle of attack is 0°, CKDO-tran can better predict the transition image of the two lobes; when the angle of attack is 4°, the transition line yielded by CKDO-tran starts too early, but the transition pattern is similar to the measurements. Therefore, CKDO-tran model is promising and deserves further development. The sensitivity study of inflow turbulence intensity shows that, along with the decrement of inflow turbulence intensity, the predicted transition pattern gradually deviates from the true pattern for the 4° attack angle case. Finally, the attack angle effect is analyzed, and it is speculated that accurate modeling of the freestream turbulence-shock interaction is the key to eliminate the attack angle effect.
- transition model /
- turbulence model /
- cross-flow transition /
- hypersonic /
- compressibility effect

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图 1 平板表面摩阻分布

Figure 1. Skin friction distribution on the flat plate

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图 2 HIFiRE-5模型三维示意图

Figure 2. 3D model of HIFiRE-5

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图 3 HIFiRE-5结构网格示意图

Figure 3. Structured mesh of HIFiRE-5

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图 4 Case3转捩图像

Figure 4. Transition pattern of Case3

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图 5 Case1转捩图像

Figure 5. Transition pattern of Case1

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图 6 Case2转捩图像

Figure 6. Transition pattern of Case2

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图 7 Case4转捩图像

Figure 7. Transition pattern of Case4

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图 8 湍流度对转捩的影响

Figure 8. Effect of turbulence intensity on transition

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表 1 HIFiRE-5模型实验工况

Table 1. Experimental setup of HIFiRE-5

Case Re/10⁶ $\alpha$/(°) Tu

1 6.1 0 2.4%
2 8.1 0 2.1%
3 10.2 0 1.8%
4 8.1 4 1.8%
5 8.1 4 1.2%
6 8.1 4 0.9%

下载: 导出CSV

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