攻角是影响后掠机翼边界层横流稳定性的关键参数之一.以NACA0012翼型为研究对象,通过求解三维可压缩Navier-Stokes方程计算了展向无限长后掠机翼的基本流场;通过求解Orr-Sommerfeld方程得到了扰动波的中性曲线及增长率演化曲线,基于线性稳定性理论(LST)研究了攻角对后掠机翼边界层流动稳定性的影响;最后采用转捩预测eN方法进行了转捩预测.研究发现,扰动波的增长在背风面受到抑制,在迎风面受到增强;转捩首先发生在迎风面,当扰动速度为来流速度的0.05%时,转捩发生的N值在6左右,转捩发生的位置在0.1~0.2个弦长之间. The angle of attack (AOA) is one of the key parameters that affect the stability of the cross-flow in the swept wing boundary layer.Based on the NACA0012 airfoil, the basic flow field of infinite swept wing is calculated by solving the three-dimensional compressible Navier-Stokes equations The neutral curve and growth rate curve of the perturbation wave were obtained by solving the Orr-Sommerfeld equation. Based on the linear stability theory (LST), the influence of angle of attack on the flow stability of the swept wing boundary layer was studied. Finally, The prediction of the eN method is based on the prediction of the turbulence.It is found that the increase of the disturbance wave is suppressed on the leeward side and is enhanced on the windward side.The turbulence first occurs on the windward side and when the turbulence rate is 0.05% The occurrence of N value of about 6, the transition occurred in the 0.1 to 0.2 chord length between.