Effect of attack angle on stability and transition in a swept-wing boundary layer

被引：0
作者：
Jing, Zhenrong [1 ]
Sun, Pengpeng [1 ]
Huang, Zhangfeng [1 ,2 ]
机构：
[1] Department of Mechanics, Tianjin University, Tianjin
[2] State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center, Mianyang
来源：
Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics | 2015年 / 41卷 / 11期
关键词：
Attack angle; eN method; Hydrodynamic stability; Swept-wing; Transition;
D O I：
10.13700/j.bh.1001-5965.2014.0769
中图分类号：
学科分类号：
摘要：
Attack angle is one of the key parameters to the cross-flow instability of swept-wing boundary layers. For swept NACA0012 airfoil with infinite spanwise length, the basic flow field was calculated by solving the three-dimensional compressible Navier-Stokes equations numerically, the neutral curve and the evolution curve of growth rate were obtained by solving the Orr-Sommerfeld equation, the effect of attack angle on the cross-flow stability was analyzed by linear stability theory (LST), and the transition position was predicted by eN method. It is found that, the growth of unstable waves in the leeward is inhibited but enhanced in the windward. Transition firstly occurs in the windward, and the transition position predicted by eN method is about 0.1 to 0.2 of the chord length with the N factor of about 6 when the disturbance velocity is 0.05% of the free-stream velocity. © 2015, Beijing University of Aeronautics and Astronautics (BUAA). All right reserved.
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页码：2177 / 2183
页数：6
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