Aerothermoelasticity of 2D shell with Finite Volume and Gallerkin Method

The panel flutter is concentrated with aerospace researchers, because of fatigue failure on structures. The usage of the numerical simulation is good company with analytical method. The 2D cylindrical panel flutter is simulated with navierstocks equations for fluid flow with finite volume theory. Also, Simulation is prepared with piston theory for analytical solution. Comparison of full numerical finite volume and assume mode method in post flutter domain is produced. Non-linear shell with the effect of in-plane load, thermal load and aerodynamic load with 3rd order piston theory is modeled to solve with assume mode method. The numerical method is 4th order rung-kutta to solve ODEs. With increasing shell camber, limite cycle oscillation change to random motion. The effect of expansion waves made decrease in second half of shell in analytical method in compare to numerical. The most important output depend on equal result for flat plate and different result on curve plate with numerical and analytical method. With increasing shell camber, limite cycle oscillation change to random motion. The effect of expansion waves made decrease in second half of shell in analytical method in compare to numerical. Amplitude of oscillation and flutter speed respectively is increase and decrease in numerical method despite of analytical one.