Nacelle for a turbojet engine with a variable nozzle

A nacelle for a turbojet engine having a downstream section comprising at least one cowling ended by at least one hinged flap forming a nozzle,

• wherein said at least one hinged flap is pivotally and translatably hinged relative to said at least one cowling;
• wherein the nacelle comprises at least one guide rail, and
• a rotation pad coupled to the nacelle is rotatable relative to the guide rail;
• wherein said at least one hinged flap comprises at least one rotation index configured to cooperate with the rotation pad, and when said at least one hinged flap is in a nominal position, said at least one rotation index is received inside a notch of the rotation pad;
• and
• wherein said notch opens onto said at least one guide rail, and said at least one guide rail is configured to receive the rotation index from the notch and to guide said at least one hinged flap in translation during a variation of the nozzle by translation of said at least one hinged flap.