考虑气动力修正的操纵面颤振特性研究
Control Surface Flutter Characteristic Study Considering Aerodynamic Correction

机翼在后缘操纵面带有大偏角时会发生一定程度的气流分离。采用计算流体力学方法计算大偏角操纵面上的气动力，并以此对采用偶极子格网法得到的气动力进行修正，进而进行机翼颤振分析。算例结果显示，气动力修正并不改变操纵面颤振模态的耦合类型，主导颤振的模态仍为机翼一弯和外段操纵面旋转；考虑操纵面偏转情况下的气动力修正后，计算得到的颤振速度比气动力未修正的结果高。
Flutter characteristic analysis for the aeroelastic system with large control surface deflection at the trailing edge of a wing is studied, where airflow separation may occur. Computational fluid dynamics (CFD) technique is adopted to obtain the aerodynamic forces on the control surface with large deflection, then the aerodynamic forces obtained by doublet lattice method (DLM) are corrected by using these data from CFD, and finally wing flutter characteristics are obtained. Aerodynamic force corrections on control surface show no effect on the calculated flutter type of the aeroelastic system for the present model, in which the flutter type obtained with and without control surface aerodynamic correction is coupled flutter from both wing bending and outboard control surface deflection. The flutter speed obtained with aerodynamic correction is higher for the present model