AIRCRAFT WITH A FUSELAGE ACCOMMODATING AN UNDUCTED TURBINE ENGINE
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United States of America Patent
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Issued Date -
Sep 26, 2024
app pub date -
Jun 5, 2024
filing date -
Jun 8, 2022
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Abstract
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: h/L.
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