黄章峰, 逯学志, 于高通. 机翼边界层的横流稳定性分析和转捩预测[J]. 空气动力学学报, 2014, 32(1): 14-20. DOI: 10.7638/kqdlxxb-2012.0062
引用本文: 黄章峰, 逯学志, 于高通. 机翼边界层的横流稳定性分析和转捩预测[J]. 空气动力学学报, 2014, 32(1): 14-20. DOI: 10.7638/kqdlxxb-2012.0062
HUANG Zhangfeng, LU Xuezhi, YU Gaotong. Crossflow instability analysis and transition prediction of airfoil boundary layer[J]. ACTA AERODYNAMICA SINICA, 2014, 32(1): 14-20. DOI: 10.7638/kqdlxxb-2012.0062
Citation: HUANG Zhangfeng, LU Xuezhi, YU Gaotong. Crossflow instability analysis and transition prediction of airfoil boundary layer[J]. ACTA AERODYNAMICA SINICA, 2014, 32(1): 14-20. DOI: 10.7638/kqdlxxb-2012.0062

机翼边界层的横流稳定性分析和转捩预测

Crossflow instability analysis and transition prediction of airfoil boundary layer

  • 摘要: 通过求解经典O-S方程(LST)、扩展的O-S方程(EOS)和线性抛物化稳定性方程(LPSE),对展向无限长、后掠角25°、迎角0°、来流Mach数0.8、单位Reynolds数6.79×106/m的机翼边界层进行了稳定性分析,结合eN方法进行了转捩预测。研究发现无限长后掠机翼在(x,ω)平面上的中性曲线没有下支,在(x,β)平面上的中性曲线呈反拇指的形状,横流不稳定性在机翼前缘占主导作用。当外界扰动进入边界层后,幅值将被直接放大,对于频率相同的扰动,首先是展向波数β大的增长起来,演化到一定位置开始衰减,然后是展向波数β小的逐渐增长起来,并且增长的指数N逐步超过波数大的扰动。转捩在机翼前缘完成,引起转捩的扰动波的展向波长约为2mm。

     

    Abstract: Crossflow instability analysis and transition prediction have been done on a 25° swept, 0° attacked airfoil with Mach number 0. 8, unit Reynolds number 6.79×106/m by solving the classic O-S equation (LST), extended O-S equation (EOS) and linear parabolic stable equation (LPSE) together with the eN method. Results show that the lower branch of the neutral curve in (x, ω) plane does not exist and the shape of the neutral curve in (x, β) plane appears as an antithumb. The crossflow instability plays a key role in the leading edge. As disturbances enter the boundary layer, their amplitude will be enlarged directly. For the same frequence, the disturbances with big wave number β will grow firstly and propogate to a certain place where they begin to decay, then the disturbances with small wave number  β  increased gradually and their increasing factor  N  will exceed that with big wave number finally. Transition occurs in the leading edge of the airfoil and the wave lengh of the inducing wave is about 2mm.

     

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