For pure pitching motion, the results show that average drag coefficient decreases as airfoil thickness is reduced.
在低雷诺数条件下，对于纯俯仰运动，随着翼型厚度的减小，平均阻力系数也变小。
As airfoil thickness is increased, the average pressure drag, affected by leading edge vortex is reduced even to be negative, and meanwhile friction has little increase.
由于前缘涡的影响，翼型厚度增加，平均压差阻力系数变小，甚至会出现负值。
A numerical method is given to calculate the unsteady lift, pitching moment and drag acting on an airfoil of rotors under attached-flow conditions in a compressible flow.
基于附着流状态下的旋翼非定常翼型气动模型，给出了计算该状态下的翼型非定常升力、阻力和俯仰力矩的数值计算方法。
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