The invention relates to an aircraft fuselage comprising a front part (2) with a cockpit, a central part (4) and a rear part (6). The central part of the fuselage includes a first zone (10) which is located at the front part and which increases in width to a maximum width towards the rear of the aircraft, a second zone (12) that decreases in width, and a third zone (14) which has an essentially constant width and which is located behind the second zone (12), width being measured along the pitch axis.
