A comparative analysis of traditional and morphing flaps for fixed-wing aircraft

Morphing wing technologies are increasingly investigated to improve aircraft efficiency and reduce the environmental impact of aviation. This thesis presents a comparative analysis between a traditional single-slotted hinged flap and a seamless morphing trailing-edge flap applied to the wing of a fixed-wing aircraft. The objective is to evaluate the performance trade-offs between conventional multi-element high-lift systems and continuous morphing geometries in terms of lift generation, drag mechanisms, and stall behavior. A structured computational methodology was developed to perform the analysis. The workflow includes geometry reconstruction using Component Cross-Section modeling, structured mesh generation with controlled refinement, mesh verification through a Grid Convergence Index study, and simulations performed with the Altair FlightStream viscous-coupled panel-method solver. The results show that the morphing configuration improves efficiency in the linear lift regime by eliminating geometric discontinuities such as flap gaps and hinge lines, which reduces parasite drag. The morphing wing also produces higher static lift at zero angle of attack for large camber settings. However, the absence of the slot effect leads to earlier boundary-layer separation at high deflection angles, resulting in reduced stall margins compared with the traditional slotted configuration. Overall, seamless morphing trailing-edge concepts can provide efficiency benefits for aircraft operating at low-to-moderate lift conditions, while requiring careful envelope management during high-lift flight phases.