FAN BLADE FOR A TURBOJET OF AN AIRCRAFT HAVING A CAMBERED PROFILE IN THE FOOT SECTIONS

摘要

The invention concerns a fan blade (4) for a turbojet of an aircraft, comprising a blade (6) that extends axially between a leading edge (18) and a trailing edge (20) and comprising a plurality of blade sections (S) stacked radially between a foot section (Spied) and a head section (Stête). All the blade sections comprised between the foot section (Spied) and a blade section (S30) positioned at a radial height corresponding to 30% of the total radial height of the blade have a skeleton curve having an inflection point.