Simulation-Based Transition Maneuver Analysis of a Convertible UAV

This study presents the nonlinear aerodynamic modeling of a convertible uncrewed aerial vehicle (CUAV) designed for operation in constrained environments, integrating the advantages of fixed-wing and rotary-wing flight. The CUAV is capable of vertical takeoff and landing (VTOL) and smoothly transitions to horizontal flight after reaching a target altitude. The vehicle features a propulsion system, vertical stabilizer, and tapered wing configuration to mitigate the effects of the wingtip vortex and improve aerodynamic efficiency. The transitional flight behavior is analyzed across a range of angles of attack to represent different flight regimes. The nonlinear model incorporates Reynolds-averaged Navier–Stokes (RANS) equations, evaluating both one-equation and two-equation turbulence models to assess turbulent viscosity effects. Simulations using computational fluid dynamics (CFD) are performed to assess the CUAV configuration, with particular emphasis on the impact of turbulence modeling on aerodynamic performance. The results confirm the vehicle capability to operate efficiently across the full flight envelope.