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.