| 摘要 |
<p>The invention relates to a nacelle for a dual-flow turbojet engine includes a cold airstream (16) having a non-constant cross-section over the periphery of the nacelle, such that at least one flap (34) is radially offset with respect to the central axis of the turbojet engine, relative to the adjacent flaps (34). The system for driving the radially offset flaps (34) is suitable for ensuring that the kinematics of said flaps (34) are offset relative to the kinematics of the flaps (34) mounted along the remainder of the periphery of the airstream.</p> |
