Computational study of aerodynamic effects in multi-propeller distributed propulsion aircraft

This study explores the aerodynamic performance and validation of a Distributed Propulsion System (DPS) – where multiple small propulsors are distributed along the wing span – using computational approaches. The primary objective is to understand how varying numbers of distributed propellers can influence aerodynamic forces, particularly lift and drag, to improve aircraft efficiency. To address these, a test model of a wing designed with distributed propellers is analyzed through CFD simulations conducted in ANSYS Fluent and SimScale, replicating realistic flight conditions. Three configurations of aircraft with two, four, and six propellers are compared. Among these, the six-propeller configuration and NACA 66–212 demonstrated the best aerodynamic performance, achieving the highest lift coefficient ( C L ) of 2.2 and a drag coefficient ( C D ) of 0.447. Such advancements hold broad potential for improving the performance, sustainability, and operational range of UAVs, eVTOLs, and next-generation eco-friendly air transportation systems.