This paper deals with the problemof the aeroelastic stability of a typical aerofoil section with two degrees of freedom induced by the
unsteady aerodynamic loads. A method is presented to model the unsteady lift and pitching moment acting on a two-dimensional
typical aerofoil section, operating under attached flow conditions in an incompressible flow. Starting from suitable generalisations
and approximations to aerodynamic indicial functions, the unsteady loads due to an arbitrary forcing are represented in a statespace
form. From the resulting equations of motion, the flutter speed is computed through stability analysis of a linear state-space
system. |