Aerodynamic and Structural Aspects of a Distributed Propulsion System for Commuter Airplane

In this paper, an aerodynamic and structural computation framework was produced to develop a more efficient aircraft configuration considering wing with distributed electric propulsion its use in different flight missions. For that reason, model of regional airplane used as case study. The considered nine-seat light cruise speed 500 km/h at altitude 9000 m. design the system is introduced, then aspects new are calculated, finally performances calculated for purpose analysis DEP effect. aimed meeting required landing conditions masses components, such motors, control units power source were estimated. Aerodynamic calculations included computations aspect ratios. These take into account drag existing parts fuselage tail surfaces. A modified lifting-line theory computational tool preliminary It calculate regime determine distribution forces moments. Next, based on envelope, basic skeletal designed weight calculated. Finally, fuel consumption sizes made compared original design. results show 35% reduction area can reduce by than 6% while keeping same overall aircraft.