壁面温度条件对边界层转捩预测的影响

孔维萱; 阎超; 赵瑞

doi:10.7527/S1000-6893.2013.0185

航空学报 >

2013 , Vol. 34 >Issue 10: 2249 - 2255

DOI: https://doi.org/10.7527/S1000-6893.2013.0185

流体力学与飞行力学

壁面温度条件对边界层转捩预测的影响

孔维萱 ,
阎超 ,
赵瑞

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北京航空航天大学航空科学与工程学院, 北京 100191

孔维萱女, 博士研究生。主要研究方向: 计算流体力学, 转捩模式。 Tel: 010-82318071 E-mail: weixuankong@163.com;阎超男, 博士, 教授, 博士生导师。主要研究方向: 空气动力学, 计算流体力学。 Tel: 010-82317019 E-mail: yanchao@buaa.edu.cn

收稿日期: 2012-11-07

修回日期: 2012-12-25

网络出版日期: 2013-02-26

基金资助

国家"973"计划(2009CB72414)

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Effect of Wall Temperature on Boundary Layer Transition Prediction Using Transition Model

KONG Weixuan ,
YAN Chao ,
ZHAO Rui

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School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China

Received date: 2012-11-07

Revised date: 2012-12-25

Online published: 2013-02-26

Supported by

National Basic Research Program of China (2009CB72414)

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摘要

边界层的转捩预测是高超声速飞行器气动力和热防护设计的关键问题之一。基于此,研究了壁面温度条件对采用转捩模式预测边界层转捩的影响,对k-ω-γ转捩模式的时间尺度和间歇因子生成项进行了修正。在非湍流脉动概念所模化的不稳定扰动时间尺度中,考虑了壁面温度条件对流动转捩的影响,引入壁面冷却对不稳定扰动最大增长率、临界雷诺数等量的模化。采用修正后的k-ω-γ转捩模式计算高超声速小球头锥零迎角流动转捩问题,通过与稳定性分析和原始k-ω-γ转捩模式计算结果的对比,发现改进后的模式在绝热和等温两种壁温条件下,能够较为准确地模拟第一模态和第二模态的不稳定频率、最大增长率,并能正确预测转捩位置。

关键词： 壁面温度; 转捩模式; 边界层; 流动转捩; 高超声速流动

本文引用格式

孔维萱 , 阎超 , 赵瑞 . 壁面温度条件对边界层转捩预测的影响[J]. 航空学报, 2013 , 34(10) : 2249 -2255 . DOI: 10.7527/S1000-6893.2013.0185

Abstract

The correct prediction of boundary layer transition is essential for a successful design of hypersonic flying vehicles. In this paper, the effect of wall temperature condition on boundary layer transition prediction using a transition model is studied. Modifications are made to the time scale based on non-turbulence kinetic energy and the production term of the intermittency factor equation of k-ω-γ transition model. The effects of wall temperature condition on the maximum amplification rate and critical Reynolds number are considered when modeling the first and second mode. The influence of wall temperature on a hypersonic boundary layer of a blunt cone with small nose bluntness at zero angle of attack is investigated by the modified k-ω-γ transition model. The improved model can provide reasonable results for the maximum amplification rate and the most unstable frequency of the first oblique and two-dimensional second mode both at adiabatic and isothermal wall conditions. The transition locations predicted by the modified k-ω-γ transition model agree well with those obtained by stability analysis.

Key words： wall temperature; transition model; boundary layer; transition flow; hypersonic flow

参考文献

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