准确数值模拟机翼动态失速时非定常流场主要有湍流模型和数值算法两方面的难点。在研究湍流模型的基础上 ,采用了 q-ω低 Reynolds数双方程湍流模型 ,并采用了一种高精度、高分辨率的数值计算方法 (L U- SGS- GE隐式算法和四阶 MUSCL TVD格式 )数值模拟了振动机翼周围的附着流动、轻度失速和深度失速非定常流场。结果表明 :采用本方法计算附着流动和轻微失速状态流场时 ,其升力系数迟滞曲线和阻力系数迟滞曲线与实验结果吻合得令人满意。深度失速的计算精度比前人工作有明显改善 Accurate numerical simulation of the unsteady flow field in the dynamic stall of the wing mainly has two difficulties in turbulence model and numerical algorithm. Based on the study of the turbulence model, a q-ω low Reynolds number two-equation turbulence model was adopted and a high-precision and high-resolution numerical calculation method (L U-SGS-GE implicit algorithm and fourth order MUSCL TVD) numerical simulation of the attachment of the flow around the wing vibration, light stalls and deep stall unsteady flow field. The results show that the hysteresis curve of the lift coefficient and the drag coefficient of the lift coefficient coincide with the experimental results satisfactorily when this method is used to calculate the flow in the adherent flow and the slightly stalled state. The calculation accuracy of deep stall is obviously improved than the previous work