Panel Flutter: one more challenge in supersonic fligth

Abstract

In the present research, it is studied the aeroelastic instability of panels in supersonic fl ow with structural nonlinearity, employing one of the expansions of the perturbations method, known as multiple time scales method. The effect of some elements, such as pre-stress, is investigated. The distinctive equations of large defl ections of a beam and the von Kármán equations for plate theory are used for the problem formulation. The Finite Element Method is applied to solve these equations. The results obtained with the program are presented as limit cycles, and they are discussed and compared to previous investigations