The nonlinear fluttercalculation demonstrates the validity of the presented method.
机翼的非线性颤振计算表明了方法的有效性。
2
A local form of interface interpolation method for fluid-structure interaction problems was presented and applied to interpolation of wing fluttercalculation.
提出了一种局部形式的流固耦合问题界面插值方法，并应用于机翼颤振计算的界面插值。
3
The unsteady aerodynamic results of the transonic wing are presented, and fluttercalculation is made. The comparison with TDLM shows that the agreement is very good.