| 摘要 |
The invention relates to a nacelle (12) for an aircraft high-bypass jet e ngine, in which a jet engine having a longitudinal axis (X) is mounted, the nacelle including a wall (24) concentrically and at least partially surround ing the jet engine and defining with the latter an annular duct (26) for the fluid inner flow, comprising at the downstream end (26a) of said nacelle wa ll a passage section of the flow outlet, characterised in that the nacelle i ncludes displacement means (42) for displacing on request a portion (24b) of the nacelle wall in order to modify the passage section of the flow outlet through which a major portion of the flow (Fi') escapes, said displacement f orming in the nacelle wall at least one opening (28; 53) through which a sma ll portion of the flow, called the leak flow (Fi '), naturally escapes, the nacelle further comprising a fluid device (30; 54) that uses a fluid for com pelling the leak flow to flow along the outer face (24e) of the portion of t he nacelle wall located downstream relative to said at least one opening.</S DOAB>
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