공력 간섭효과를 고려한 Wing/Tail 형상에 대한 비선형 공탄성 해석

Abstract

In this study, a nonlinear aeroelastic analysis system for general wing/tail configurations has been developed using the numerical techniques of computational fluid dynamics and computational structural dynamics. The flutter characteristics of tail wing can be varied largely due to the effect of downstream generated from the forward lifting surface. The present analyses have been performed in the subsonic, transonic and supersonic flow regions to consider the various nonlinear shock wave effects. The flutter analysis results for various horizontal and vertical separation distances are presented to illustrate wing/tail interaction flutter mechanism. It is also shown in the transonic flow region that the limit cycle oscillations can occur on tail wing due to the nonlinear unsteady downstream.