Abstract: In this study, the effect of rotating vanes, installed on the body of the Coanda UAV is investigated both experimentally and numerically, with the aim of improving its aerodynamics performance. By constructing and testing two models of Coanda UAVs with and without axial vanes, for measuring the lift and dynamic pressure distribution on the body, 16% increase in lift is observed. In addition, a finite volume solver is utilized to investigate the flow over Coanda UAVs with and without rotating vanes. Numerical results show that the installed axial vanes on the Coanda UAV leads to increasing lift about 21%. The numerical results are in good agreement with the experiments. Overall, the results show that mounting axial vanes on the body of Coanda UAV increase lift. The consequences of installing an axial vane at the separation point of the fuselage surface on the overall lift of the Coanda UAV are discussed.