Numerical Investigation of the Aerodynamics of a Propeller-Driven Transition Micro Aerial Vehicle

This numerical investigation examines the impact of propeller slipstream on the aerodynamic performance of a fixed-wing Transition Micro Aerial Vehicle (TMAV). Computational simulations were performed at a freestream velocity of 15 m/s, encompassing a range of angles of attack from -8˚ to 16˚. The study considered a propeller rotation speed of 6000 rpm and tail fin deflection angles of 0˚, -16˚, and 16˚. The TMAV configuration comprises a cylindrical body, rectangular wings, and an X-tail control fins assembly. The multiple reference frame (MRF) technique was used to simulate the coupled TMAV and propeller induced flow field. Based on the tail surface deflection angles, three distinct maneuvering conditions were defined; level flight maneuver (LFM), pitch-down maneuver (PDM), and pitch-up maneuver (PUM). The analysis reveals that the propeller slipstream significantly alters the local angle of attack on the wings and X-tail surfaces partially immersed in the slipstream, leading to a reduction in lift coefficients and an increase in drag coefficients on control surfaces. Under LFM and PUM conditions, the slipstream induces lower lift and higher drag forces, whereas PDM conditions exhibit enhanced lift and reduced drag. The aerodynamic modifications induced by propeller slipstream effects significantly degrade the overall aerodynamic efficiency and result in adverse pitching moment characteristics under most maneuvering conditions. A detailed evaluation of individual component contributions to the overall aerodynamic parameters reveals substantial variations in the aerodynamic behavior of both the wing and X-tail configurations when subjected to slipstream-influenced freestream conditions of the TMAV.