Flattened nacelle of a turbojet engine

A nacelle, comprising:

• an outer structure provided with a thrust reverser device and a front frame;
• and
• an inner structure covering a downstream section of a turbojet engine, the outer structure and the inner structure defining a flow stream of an air flow of the turbojet engine,
• the thrust reverser device comprising:
• one movable cowl translating along a direction parallel to a longitudinal axis of the nacelle, the movable cowl configured to alternately switch from a closing position to an opening position, wherein in the closing position, the movable cowl provides aerodynamic continuity of the front frame, and in the opening position, the movable cowl opens a passage in the nacelle for the air flow to be diverted, the movable cowl having a non-constant cross section over a periphery of the flow stream of the air flow;
• and
• a cascade for diverting at least one part of the air flow of the turbojet engine through the passage, the cascade being mounted on the front frame at an upstream end thereof,
• wherein a connection of the front frame and the diversion cascade being mounted on a reduced cross-sectional area of the movable cowl is centered on a first axis offset relative to a second axis on which a connection of the front frame and the diversion cascade being mounted on a remainder of a periphery of the movable cowl is centered.