Nonlinear Flutter Analysis of Curved Panel under Mechanical and Thermal Loads Using Semi-Analytical and Finite Volume Methods

The vibration behavior of components exposed to aerodynamic loads must be taken into consideration when designing aerial vehicles. Numerical simulation plays a key role in developing more realistic analytical models for panel flutter analysis. The notable feature of the present research is the use of two methods for the aeroelastic analysis of two-dimensional curved panels with cylindrical bending. In the first approach, the finite volume method (FVM) is used for supersonic viscous flow and nonlinear structural model while full Navier-Stokes equations are discretized. In the second approach, the third-order nonlinear piston theory aerodynamics in addition to mechanical and thermal loads is assumed. Moreover, the semi-analytical weighted residual method for the nonlinear curved panel is utilized. These approaches are concurrently compared with each other for the first time. Furthermore, Hamilton’s principle is used and partial differential equations (PDEs) are derived. The effects of geometric curvature on the flutter and post-flutter behavior of the panel are compared for both methods. During the flutter, the pressure distribution over the curved panel is calculated for viscid and inviscid flows. The agreement and discrepancy between semi-analytical and finite volume solutions for the flutter analysis such as bifurcation diagrams are remarkable. The flutter boundary and post-flutter amplitude of the curved panel in the FVM are less than those in the semi-analytical method. The effect of plate curvature is investigated by combining thermal and in-plane loads accurately and comprehensively.