k-ω-γ模式对转捩影响因素的预测性能研究

郝子辉; 阎超; 周玲

doi:10.6052/0459-1879-14-294

k-ω-γ模式对转捩影响因素的预测性能研究

doi: 10.6052/0459-1879-14-294

北京航空航天大学航空科学与工程学院, 北京100191

基金项目: 国家973 计划资助项目(2009CB72414).

详细信息

通讯作者:
阎超,教授,主要研究方向:计算流体力学.E-mail:yanchao@buaa.edu.cn

中图分类号: V211.3
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出版历程
- 收稿日期: 2014-09-24
- 修回日期: 2014-12-11
- 刊出日期: 2015-03-18

PARAMETRIC STUDY OF A k-ω-γ MODEL IN PREDICTING HYPERSONIC BOUNDARY-LAYER FLOW TRANSITION

School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

Funds: The project was supported by the National 973 project (2009CB72414).

摘要

摘要: 高超声速边界层转捩的准确预测对飞行器的防热、减阻至关重要,而影响高超声速边界层转捩的因素众多.从模式角度出发研究边界层转捩的影响因素,采用k-ω-γ 转捩模式对5°圆锥的边界层转捩进行了数值分析,计算了不同头部钝度、来流雷诺数和湍流度情况下的边界层转捩,并与实验结果进行了对比. 研究结果表明:k-ω-γ 转捩模式基本能够反映头部钝度、来流雷诺数、来流湍流度对高超声速圆锥边界层转捩的影响规律,但对转捩后的热流峰值预测不准;从模式构造角度分析发现,雷诺数越高或头部钝度越小,层流区边界层越薄,k-ω-γ 转捩模式中第一、第二模态时间尺度增大,因此转捩起始位置提前;来流湍流度越大,等效脉动动能初值越大,导致层流区发展过程中等效脉动动能越大,因此转捩易于发生.
- k-ω-γ 模式 /
- 转捩 /
- 圆锥 /
- 头部钝度 /
- 来流湍流度
Abstract: Predicting hypersonic boundary layer transition accurately is important to thermal protection and drag reduction of vehicle. However, many factors affect the process of hypersonic boundary layer transition. To study the impact factors of boundary layer transition from the transition model aspect, simulations on boundary layer transition of a 5° cone were carried out by using k-ω-γ transition model under different nose bluntness, frees-steam Reynolds numbers (Re_∞) and turbulence intensities (FSTI), and compared with the wind tunnel results. Some conclusions were obtained: k-ω-γ transition model can basically reflect the effects of nose bluntness, Re_∞ and FSTI on hypersonic boundary layer transition, however not well in predicting the heat peak following the transition; from the view of formulation of transition model, reducing the nose bluntness or increasing the Reynolds number can decrease the boundary layer thickness, which leads to the increase of the time scales of both the first mode and the second mode, and then the transition occurs prematurely; the FSTI is larger, the equivalent fluctuation kinetic energy is stronger in the laminar zone of the boundary layer, and boundary layer transition takes place easily.
- k-ω-γ model /
- transition /
- cone /
- nose bluntness /
- free-stream turbulence intensities

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参考文献(17)

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