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Finite Element Simulation of Aircraft Wing with Fluid-Structure Interaction

Abstract:

This research compares the results obtained by the computational simulation of the DA20-C1 aircraft wing made of GFRP composite materials with a rigid foam core, versus the mechanical properties of the original aircraft material. Associated computational fluid dynamics (CFD) techniques and finite element analysis (FEA) were performed to obtain the simulation of fluid-structure interaction. As result, the coefficient of lift and resistance of the aerodynamic profile were obtained to simulate the pressure and velocity gradients around the aeronautical component. This result was compared to the mechanical properties of the wing, by calculating the total deformation in critical flight conditions and the resulting equivalent stresses. The study was validated by verifying that the mechanical properties of the sandwich-type composite material, belong to the airfoil DA20-C1 aircraft wing, have a directly proportional relationship to the results of the computational simulation done by finite elements and the fluid-structure relationship. As a result, a new methodology of inverse engineering was found for repairing aeronautical structural components.