高超声速飞行器前体边界层强制转捩数值模拟

doi:10.7527/S1000-6893.2013.0480

流体力学与飞行力学

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高超声速飞行器前体边界层强制转捩数值模拟

周玲, 阎超, 孔维萱

北京航空航天大学航空科学与工程学院, 北京 100191

收稿日期:2013-07-29 修回日期:2013-11-28 出版日期:2014-06-25 发布日期:2013-12-17
通讯作者: 阎超，Tel.：010-82317019 E-mail：yanchao@buaa.edu.cn E-mail:yanchao@buaa.edu.cn
作者简介:周玲女，博士研究生。主要研究方向：计算流体力学，转捩模式。Tel：010-82317523E-mail：zhouling@ase.buaa.edu.cn；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：010-82317019E-mail：yanchao@buaa.edu.cn
基金资助:
国家“973”计划（2009CB72414）

Numerical Simulation of Forced Boundary Layer Transition on Hypersonic Vehicle Forebody

ZHOU Ling, YAN Chao, KONG Weixuan

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

Received:2013-07-29 Revised:2013-11-28 Online:2014-06-25 Published:2013-12-17
Supported by:
National Basic Research Program of China (2009CB7414)

摘要/Abstract

摘要：

边界层强制转捩是保证超燃冲压发动机进气道正常启动的关键技术之一，k-ω-γ转捩模式是适用于高超声速边界层转捩预测的方法。为研究该方法对边界层强制转捩的预测性能及不同转捩带对边界层强制转捩的影响特征，对原始的k-ω-γ转捩模式进行了壁面温度影响修正，采用修正的k-ω-γ转捩模式对高超声速飞行器进气道前体边界层强制转捩进行数值分析，计算了光滑外形、钻石型转捩带外形和斜坡型转捩带外形在马赫数Ma=6，7条件下的边界层转捩，并与试验结果进行了对比。研究结果表明，修正的k-ω-γ转捩模式对边界层强制转捩具有较好的预测能力，计算得到的转捩起始位置与试验结果基本吻合。两种转捩带强制转捩效果明显，其中：钻石型转捩带产生的扰动强于斜坡型转捩带，且转捩区长度较斜坡型转捩带短；斜坡型转捩带在控制边界层流动分离、减小流动横向溢出效果上优于钻石型转捩带。

关键词: 高超声速飞行器, 边界层, 强制转捩, 转捩模式, 转捩带, 壁面温度

Abstract:

Forced boundary layer transition is a key technology to ensure scramjet normal start, and the k-ω-γ transition model is an effective way to predict hypersonic boundary layer transition. To study the prediction performance of the k-ω-γ transition model on forced boundary layer transition and the effects of different trips on boundary layer transition, a wall temperature effect modification is conducted on the original k-ω-γ transition model, and the modified k-ω-γ transition model is employed to investigate the forced boundary layer transition ona hypersonic vehicle forebody. The transition onsets of forebodies with no trip, with diamond trips and with ramp trips under Mach 6 and 7 are studied by numerical simulation, and the results are compared with those from the experiment. It is found that the modified k-ω-γ transition model can well predict forced boundary layer transition, and the transition onset locations of numerical simulation are consistent with experiment results. Both diamond trips and ramp trips can obviously promote boundary layer transition forward to reduce flow separation and lateral flow spillage. Disturbances caused by diamond trips are stronger than those by ramp trips, and the transition length is shorter than that of ramp trips as well. However, ramp trips show a better performance on controlling boundary layer flow separation and reducing lateral flow spillage compared with diamond trips.

Key words: hypersonic vehicle, boundary layer, forced transition, transition model, trip, wall temperature

中图分类号:

周玲, 阎超, 孔维萱. 高超声速飞行器前体边界层强制转捩数值模拟[J]. 航空学报, 2014, 35(6): 1487-1495.

ZHOU Ling, YAN Chao, KONG Weixuan. Numerical Simulation of Forced Boundary Layer Transition on Hypersonic Vehicle Forebody[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2014, 35(6): 1487-1495.

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E-mail：hkxb@buaa.edu.cn

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高超声速飞行器前体边界层强制转捩数值模拟

Numerical Simulation of Forced Boundary Layer Transition on Hypersonic Vehicle Forebody

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