Flutter Estimation for Low Speed Aircraft Wing Using Fully Coupled Fluid – Structure Interaction

The aero elastic responses and the flutter condition of 3-D flexible aircraft wing were estimated by developed fully coupled fluid-structure interaction approach. The actual wing in this approach was represented by an equivalent plate .Equivalent plate model (structure model) based on assumed mode method was then combined with unsteady panel-discrete vortex method (aerodynamic model) to build relatively simple aeroelastic model. This model could be used for estimation of flutter condition of moderate to high aspect ratio and low sweep wings of aircraft flight at low subsonic speeds. The obtained results from the present model are able to prediction the flutter condition of the actual wing at different angles of attack. The increasing in the angle of attack leads to reduce flutter speed and flutter frequency.