Abstract
In this paper the aeroelastic instability of a wing, modeled as an orthotropic composite beam with a concentrated mass subjected to the engine thrust, is investigated in an incompressible flow. The wing is modeled using classical beam theory. Wagner function is used to model the unsteady aerodynamic loads, while the engine thrust is modeled as a follower force and a concentrated mass is used to model the engine mass. The numerical results of the developed generic and simple model are compared with published results, and an excellent agreement is observed. The fiber orientation, engine thrust, mass magnitude and its location are reported to have had significant effects on the aeroelastic instability boundaries.
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