航空学报 > 2016, Vol. 37 Issue (8): 2445-2453   doi: 10.7527/S1000-6893.2016.0200

高超声速进气道强制转捩流动的大涡模拟

赵晓慧1, 邓小兵1, 毛枚良2, 杨伟1, 赵慧勇3   

  1. 1. 中国空气动力研究与发展中心 空气动力学国家重点实验室, 绵阳 621000;
    2. 中国空气动力研究与发展中心 计算空气动力研究所, 绵阳 621000;
    3. 中国空气动力研究与发展中心 高超声速冲压发动机重点实验室, 绵阳 621000
  • 收稿日期:2016-02-16 修回日期:2016-06-21 出版日期:2016-08-15 发布日期:2016-06-27
  • 通讯作者: 邓小兵,Tel.:0816-2463219。E-mail:xbdeng@skla.cardc.cn E-mail:xbdeng@skla.cardc.cn
  • 作者简介:赵晓慧,男,博士研究生,助理研究员。主要研究方向:湍流数值模拟,高超声速空气动力学。Tel.:0816-2463219。E-mail:xhzhao@skla.cardc.cn;邓小兵,男,博士,副研究员。主要研究方向:计算流体力学,湍流数值模拟。Tel.:0816-2463219。E-mail:xbdeng@skla.cardc.cn;毛枚良,男,博士,研究员,博士生导师。主要研究方向:计算流体力学,高阶精度格式,高超声速空气动力学。Tel.:0816-2463296。E-mail:mm1219@163.com
  • 基金资助:

    国家自然科学基金(11402289)

Large eddy simulation for forced transition flow at hypersonic inlet

ZHAO Xiaohui1, DENG Xiaobing1, MAO Meiliang2, YANG Wei1, ZHAO Huiyong3   

  1. 1. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000, China;
    2. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China;
    3. Science and Technology on Scramjet Laboratory, China Aerodynamics Research and Development Center, Mianyang 621000, China
  • Received:2016-02-16 Revised:2016-06-21 Online:2016-08-15 Published:2016-06-27
  • Supported by:

    National Natural Science Foundation of China (11402289)

摘要:

吸气式高超声速飞行器常在进气道边界层内布置粗糙颗粒或涡流发生器强制流动转捩为湍流以确保发动机正常启动。为了清晰认识强制转捩过程,采用隐式大涡模拟方法,对强制转捩问题开展了数值模拟研究。针对钻石形和斜坡形涡流发生器,计算得到涡流发生器诱导的流动结构,显示出强制转捩流动由涡流发生器产生的反向旋转流向涡对主导。扰动沿流向增长和发展,导致流向涡对以偶模式或奇模式失稳,偶模式失稳产生对称形式的涡对破碎,而奇模式失稳则导致非对称(弯曲)形式的涡对破碎。流向涡对破碎后产生一系列发卡涡并最终促使边界层转捩为湍流。最后就计算网格和数值耗散对隐式大涡模拟结果的影响以及计算的收敛性进行了讨论。

关键词: 高超声速, 进气道, 强制转捩, 涡流发生器, 大涡模拟

Abstract:

Forced transition is commonly used for a hypersonic air breathing vehicle to ensure its scramjet's normal start by placing roughness elements or vortex generators in the inlet boundary layer. To get a clear image of forced transition process, an implicit large eddy simulation method is used for laminar-turbulent forced transition flows in the boundary layer of a hypersonic inlet configuration. Main structures are obtained for the forced transition flows induced by the vortex generators shaped of diamonds and ramps, which show that the flows are dominated by stream-wise counter-rotating vortices. Fluctuations grow in the stream-wise direction and cause instabilities. Two fundamental modes of the instabilities are found in the simulations, the even mode and the odd one. The even mode leads to a varicose way of breaking down of the counter-rotating vortices, while the odd one leads to a sinuous way. Strings of hairpin vortices are generated after the breaking down and finally cause the transition. A discussion is carried out on the computation convergence together with the influence of the grids and numerical dissipation.

Key words: hypersonic, inlet, forced transition, vortex generator, large eddy simulation

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