An aircraft (100, 200, 300) comprising a fuselage (102, 202, 302) and an unducted turbine engine (10, 116, 216, 316). The fuselage having a divot (122, 222, 322) with an upstream edge (130, 330) and a downstream edge (132, 332). The divot is defined by a straight reference line (142), connecting the upstream edge and the downstream edge and having a length (L), and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core (44), a nacelle (40), and a set of blades (42, 118, 318). A first flow ratio (FR1) is equal to: h/L and wherein the first flow ratio is greater or equal to 0.01 and less than or equal to 0.15.
AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE
FLUGZEUG MIT EINEM RUMPF DER EINEN MANTELLOSEN TURBINENMOTOR AUFNIMMT
AÉRONEF AVEC UN FUSELAGE LOGEANT UNE TURBOMACHINE NON CARÉNÉE
13.12.2023
Patent
Elektronische Ressource
Englisch
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