Aerodynamic effects of propeller slipstream on a transition micro aerial vehicle under various maneuvering conditions

This study examines the influence of propeller slipstream on the aerodynamic performance and longitudinal static stability of the Transition Micro Aerial Vehicle (TMAV), highlighting its role in advancing design and control strategies for Micro Aerial Vehicles. The objective is to assess the impact of propeller slipstream on the aerodynamic efficiency and static stability during various flight maneuvers. Wind tunnel experiments were conducted on a fixed-wing TMAV at a freestream velocity of 15 m/s, covering three propeller advance ratios (0.65, 0.55, 0.45), angles of attack from −8° to +16°, and tail deflection angles of −8°, 0°, and 8°. Computational fluid dynamics simulations for an advance ratio of 0.45 were also performed to validate experimental findings and analyze flow physics. The results reveal that the propeller slipstream significantly influences aerodynamic performance, reducing lift and increasing drag, which degrades longitudinal stability in maneuvering conditions. Drag coefficients increased by up to 43.98%, while the maximum lift-to-drag ratio decreased by 38.66% compared to unpowered cases. Lift forces dropped by 37.86% during level flight and 19.74% during pitch-up maneuvers but rose by 25.98% in pitch-down maneuvers. The starboard wing generated consistently higher lift than the port wing due to asymmetrical aerodynamic effects from the slipstream. Variations in lift and drag on the X-tail fins were strongly affected by interactions between the slipstream and wing downwash. These findings provide critical insights for optimizing TMAV design and enhancing stability in propeller-driven flight.