Study on Two-dimensional Wing Flutter Analysis by a High-order Flux Reconstruction Method

Wing flutter analyses are carried out by a newly developed flow solution method using high-order flux reconstruction approach. The significance steps to be achieved are the moving boundary/moving grid technique in high-Reynolds number flows. The k-ω turbulence model is implemented for the objectives. The method is first validated by a forced oscillation and then fluid-structure coupled flutter simulations are carried out in subsonic flows. The predicted flutter boundary well agreed with previous numerical studies. It is found that 3rd - and 4th -order spatial accuracy produces almost the identical results in the presented cases, while the viscous effects the flutter boundary. Preliminary results in transonic flow with shock waves are also included.