An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to:hL.
Aircraft with a fuselage accommodating an unducted turbine engine
2024-07-09
Patent
Electronic Resource
English
AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE
European Patent Office | 2023
|AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE
European Patent Office | 2023
|