通过引入“网格速度”方法模拟阵风条件,求解非定常欧拉方程实现了不同展弦比0012平直机翼阵风响应的数值模拟。首先采用该方法对NACA0006翼型迎角阶跃型阵风的气动力响应进行了计算,计算结果与文献结果、理论值吻合良好。进一步对展弦比分别为5、10的0012平直机翼在迎角阶跃型、One-Minus-Cosine型阵风作用下的气动力响应过程进行了模拟分析。研究结果表明,当展弦比增大时,阵风作用下机翼的升力系数响应会增加,机翼翼根部位气动响应幅值大于翼尖部位响应特性。 By simulating gust conditions by introducing “grid velocity ” method and solving unsteady Euler equations, the numerical simulation of the gust response of 0012 straight wings with different aspect ratios is realized. First of all, the aerodynamic response of the NACA0006 airfoil with stepped gust is calculated by this method. The calculated results are in good agreement with the literature and theoretical values. The aerodynamic response of the 0012 straight wing with aspect ratios of 5 and 10, respectively, under the attack of One-Minus-Cosine gust was simulated. The results show that when the aspect ratio increases, the lift coefficient response of the wing under gust increases, and the aerodynamic response amplitude of the wing root is greater than that of the wing tip.