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
09.07.2024
Patent
Elektronische Ressource
Englisch
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