Nacelle of turbojet engine comprising inverter flap

The invention relates to a nacelle (102) for a ducted fan turbojet engine (100) comprising an engine (20). The nacelle (102) comprises a fixed cowl (206), an upstream wall (209) bounding off, with theengine (20), a working section (202) for a secondary flow (208), a movable cowl (207) with an interior wall (207a) and an exterior wall (207b), and movable in translation between a closing position where the exterior wall (207b) adjoins the fixed cowl (206) and the interior wall (207a) prolongs the upstream wall (209), and an opening position where the exterior wall (207b) is distant from the fixed cowl (206) so as to open a window (210) and the interior wall (207a) is distant from the upstream wall (209), an inverter flap (104) between the interior wall (207a) and the exterior wall (207b) mounted to be free in rotation about an axis of rotation (50) situated on the interior wall (207a) and a drive mechanism (260) for moving the movable cowl (207). 本发明涉及用于包括发动机(20)的函道风扇涡轮喷气发动机(100)的短舱(102)，所述短舱(102)包括：-固定风罩(206)，