두께변화가 있는 조종날개의 초음속 플러터해석

Abstract

The supersonic flutter analysis of a control wing has been performed. The third order piston theory has been applied for the aerodynamic calculation to consider a change of wing thickness and the finite element method has been used for the structural analysis. The flutter solution has been obtained by using V-g method. The surface spline method is used for the interpolation between structural and aerodynamic grid points of the wing. The effects of the wing thickness change on the flutter are investigated.