UNCOUPELED AERONAUTICAL PROPELLER FOR AIRCRAFT

Abstract

The aeronautical thruster (100) comprises: - an external casing (102); - a hub (104) pivotally mounted relative to the external casing (102) around a main axis (X) extending in an upstream-downstream direction of the aircraft; - a propulsive propeller (106) mounted on the hub (104) so ​​as to be pivotable relative to the external casing (102); and - a fixed rectifier (112) mounted on the external casing (102) downstream of the propulsive propeller (106) along the main axis (X), the fixed rectifier (112) extending around the main axis (X), the fixed rectifier (112) comprising stator blades (114). For at least one stator blade (114) of the fixed rectifier (112), the maximum thickness position is between 0.1 and 0.5 for all the blade heights (H') and / or the maximum thickness position (Xepmax) is strictly decreasing over at least 60% of the blade height H', preferably at least 75% of the blade height (H'). Figure for abstract: Fig. 1