翼列における失速フラッタ : 第2報, 準actuator discの方法による純曲げ振動翼理論, その2

抄録

In the 1st report fundamental equations for calculating the aerodynamic force acting on the cascading blades vibrating in a translatory mode were given. This report shows the results of the calculation and gives the criterion for the flutter (the boundary of the region where the aerodynamic damping force cannot be negative).