A numerical comparison between a morphign wing and a traditional wing: aerodynamic effects of controlled piezoelectric deflections

One of the tasks of the FutureWings project, funded by the European Commission within the 7th framework, concerned the numerical validation of the mechanical behavior of a wing whose deflections can be controlled by means a suitable distribution of piezoelectric patches. Starting from a reference geometry two wing models have been implemented and analyzed adopting a Fluid Structure Interaction analysis technique: a traditional wing with an aileron surface and a morphing wing having a self-deforming leading edge and a self-deforming trailing edge thanks to the application of piezoelectric patches. In a first case a roll maneuver has been simulated. As piezoelectric patches the Macro Fiber Composite have been used. The aeroelastic analyses have been carried out at low mach number at the sea level and at high mach number at cruise level flight. From a practical point of view, as a preliminary, the work shows what are, at present, the technical possibilities of the technology related to the application of piezoelectric materials in the primary aerostructures field.