Infinite Wing: aerodynamic analysis of a novel wing concept for UAVs

This thesis investigates the aerodynamic performance of a conceptual Intelligence, Surveillance, and Reconnaissance Unmanned Aerial Vehicle (ISR UAV) featuring an innovative closed-wing architecture, designated the "Infinite Wing." Derived from Prandtl’s "Best Wing System" theory, this configuration theoretically minimizes induced drag, presenting a prominent opportunity for enhanced aerodynamic efficiency and reduced energy consumption in aviation. The primary objective of this study is to quantify these theoretical benefits and evaluate the concept's aerodynamic behavior. The analysis encompasses preliminary aerodynamic sizing via Vortex Lattice Method (VLM), high-fidelity 3D CAD modeling, and Computational Fluid Dynamics (CFD) simulations. To validate the concept, a direct comparative analysis was performed against an equivalent conventional wing configuration. The numerical results confirm the Infinite Wing’s capacity for induced drag reduction at moderate-to-high angles of attack and demonstrate exceptional deep-stall resilience, while identifying a lift penalty in the low-incidence cruise regime. Ultimately, this study validates the aerodynamic applicability of the closed-wing concept for demanding Short Take-off and Landing (STOL) and complex multi-objective UAV missions, concluding with a brief overview of potential implications for the civil commercial aviation sector.