中文摘要：

对于翼面变形法向运动速度远小于来流速度的儒可夫斯基机翼,将解析解和离散涡方法相结合计算变形机翼的流场及非定常气动力,较详细地分析了变形机翼升力系数的准定常计算方法的误差来源,并给出修正方法。计算结果显示脱落涡尾迹对升力系数和机翼绕流环量的影响很小,变形机翼升力系数准定常计算方法的误差主要来源于流体非定常运动引起的虚拟质量力,该非定常附加升力仅与当前时刻飞行姿态及翼型形状和变形速率有关,与具体的变形历史过程无关,变形机翼的升力近似等于准定常计算结果叠加上相应的虚拟质量力。

英文摘要：

Assuming that the normal deformation velocity on the wing surface is much smaller than free stream velocity, the unsteady flow field and aerodynamic lift for the morphing Joukowski airfoil were calculated by combining the analytical solution and the discrete vortex method together. The error sources of quasi-steady assumption were analyzed rigorously and correspondingly the error correction method was proposed. The numerical calculations show that the vortex wake of morphing airfoil has almost no effect on the lift coefficient and the circulation around the airfoil. The additional unsteady aerodynamic lift caused by the virtual mass force is the main error source of quasi-steady solution for the aerodynamic lift of morphing airfoil. It is also shown that the flight attitude, the airfoil profiles and the deformation veloci- ty determine the unsteady additional lift coefficient, which has little relation with the evolutionary history of deformation. It is proposed that the lift of morphing airfoil is approximately equal to the lift of quasisteady solution adding the corresponding virtual mass force.