Supersonic panel flutter of variable stiffness composite laminated skew panels subjected to yawed flow by using NURBS-based isogeometric approach

An enhanced isogeometric finite element method is developed to investigate the free vibration analysis as well as the linear flutter characteristics of finite square as well as skew laminated plates. The laminates are assumed composed of variable stiffness plies due to implementation of curvilinear fibers. The flutter analysis of the skew laminate under various flow yaw angles are also taken into account. The first-order shear deformation plate structural assumptions are utilized in conjunction with an aerodynamic loading model according to the first-order piston theory. The cubic NURBS basis functions are employed to build the plate's geometry while are also hired as the shape functions for finite element analysis field approximations. In order to show the accuracy and effectiveness of the present formulation, some representative results are provided and compared to those available in the literature. The flutter characteristics of curvilinear skew laminates are investigated and the effects of different changing parameters including boundary condition, skewness, flow direction and layup on the dynamic stability of the panel from both free vibration as well as flutter points of view are then studied.