Investigation and Development of Distributed Propulsion UAV

Abstract

Distributed propulsion UAV is an aircraft configuration in which cross-flow fan is used in close conjunction with the fixed-wing at the leading edge. This generates good amount of lift and lowers the stalling speed as compared to that of conventional wing aircraft. This UAV does not stall at higher angle of attack. The distributed propulsion UAV offers many merits of both fixed-wing aircraft and helicopters as the fan’s tip speed is extremely low in this UAV as compared with the conventional aircraft propellers or helicopter rotors thereby increasing the propulsive efficiency and reducing the noise. In this present study, an attempt has been made to design and develop the distributed Propulsion UAV. Design is done using Solidworks and CFD analysis is carried out using Ansys. Thus, the distributed propulsion UAV that is developed will be able to take-off and land in a shorter runway at low-speed conditions and has better stalling characteristics as compared to that of conventional aircraft. A different mechanism is used to run the cross-flow fan in this study, different airfoil as well as a working model is developed.