  We propose a fully coupled numerical model to predict energy transmission
through a turbulent boundary layer (TBL) excited stiffened double-leaf flexible
aircraft panel using a finite element (FE) framework. Mindlin first order shear
deformation model is adopted for the panels and a TBL-structure-acoustic
coupling model is developed using finite element-radiation resistance matrix
(FE-RRM) approach to predict the transmission loss (TL) through double-leaf
panels with variable thickness and stiffener orientation. The model is also
capable to capture the contribution of orthotropic lamina sequence and
frequency-dependent structural damping in predicting the TL. Thus, a new
numerical model is proposed that enables the designers with greater flexibility
in terms of the number of panel leaves, boundary, and stiffening condition of
the aircraft panel-cavity-panel system, made of isotropic or orthotropic
laminates.
