An alternative beam Fe for aeroelastic analysis of flapped wings

This work aims to present an alternative time domain modeling approach for preliminary flutter analysis of wings equipped with trailing edge control surfaces. The proposed modeling approach is based on the formulation of an aeroelastic beam finite element that relies on Euler-Bernoulli beam theory and De Saint Venant torsion theory for the structural part and on Theodorsen theory for aerodynamics. The modeling approach here presented is useful for preliminary aeroelastic analysis and it could be readily implemented in existing beam finite elements-based codes.