A Computational Investigation of the Hover Mechanism of an Innovated Disc-Shaped VTOL UAV

Inventive approaches are constantly being revealed in the field of vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) configuration concepts designs. To date, a body-associated UAVs for augmented lift remains unclear among other approached The current paper investigates mechanism high-lift ducted fan mounted central body VTOL UAV We report an unresolved design disc-shaped with single rotor that aims to enhance cost-effectiveness fuel consumption substantial contribution hover thrust. convex upper surface curvature was applied generate significant from during hover. computational fluid dynamics (CFD) approach based on unstructured discretization followed by three-dimensional steady Reynolds-averaged Navier–Stokes (RANS) flow ANSYS CFX mechanistically investigate underlying considerations. uses lip duct inlet force demonstrates 95% thrust hovering. UAV’s generates prolonged entrainment free momentum losses swirling flows. This phenomenon is reduced power hovering flight, making aerodynamically stable environmentally safe.