宇航学报

宇航学报 ›› 2014, Vol. 35 ›› Issue (8): 893-900.doi: 10.3873/j.issn.1000-1328.2014.08.005

• 飞行器设计与力学 • 上一篇    下一篇

高超声速飞行器前缘缝隙流动数值模拟研究

张昊元，宗文刚，桂业伟   

  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. 四川大学化工学院，成都 610065
  • 收稿日期:2013-06-05 修回日期:2013-08-18 出版日期:2014-08-15 发布日期:2014-08-25
  • 基金资助:

    国家自然科学基金重大研究计划（91216204）

Numerical Investigation of Flow in Leading Edge Gap of Hypersonic Vehicle

ZHANG Hao yuan,  ZONG Wen gang,  GUI Ye wei   

  1. 1.State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang 621000,China;
    2.Computational Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang 621000,China;
    3.College of Chemical Engineering, Sichuan University, Chengdu 610065,China
  • Received:2013-06-05 Revised:2013-08-18 Online:2014-08-15 Published:2014-08-25

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摘要：

通过分析高超声速飞行器前缘防热瓦结构，建立了一种开缝前缘的简化模型。针对这一模型的流场通过求解三维可压缩Navier Stokes方程进行了数值模拟。研究了缝隙诱导形成的三维旋涡的空间分布特征和旋涡运动对物面气动加热的影响规律。模型圆弧段缝隙肩部倒圆区因存在较强的三维效应形成“常规”高热流区，而缝隙内主旋涡再附致使侧壁上存在一个“非常规”高热流区；模型平直段展向流动诱导缝隙上方出现较强的旋涡运动，同时流动在缝隙倒圆区形成分离涡并于缝隙侧壁面再附，受这些旋涡运动的影响，缝隙肩部倒圆区转变为局部热流低值区，缝隙侧壁上存在局部热流高值区。

关键词: 高超声速飞行器, 前缘缝隙, 气动加热, 数值模拟

Abstract:

The vertical gap flow in the wing leading edge of the hypersonic vehicle is investigated in this paper. By analyzing the structure of the leading edge shield, a geometrical model for the leading edge gap is established. The flow field structure is obtained by solving the 3D Navier Stokes equations. The spatial distribution fetature of the 3D vortex induced by gap and corresponding relations between the vortex motion and heat flux distribution are analyzed. The numerical result shows that in the circular section, the rounding zone of the gap shoulder is a local high heat flux region because of strong 3D effect normally, and the reattachment of the primary vortex in the gap leads to a “non normal” high heat flux region on the side wall of the gap. In the straight section, there is a strong vortex region above the gap induced by span wise flow. Because of the effect of vortex separation, the original local high heat flux region at the rounding zone of the gap shoulder turn to local low heat flux region, and local high heat flux region exists in the side wall region.

Key words: Hypersonic vehicle, Leading edge gap, Aerodynamic heating, Numerical simulation

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