| 摘要 |
<p>The invention relates to a nacelle for a turbojet engine, having a longitudinal axis and a rear section including an annular flow path comprising walls (110) defining a space (3, 10) through which a main air flow (12) passes. The nacelle includes at least one device (100) for modulating the cross-section of the space (3, 10), comprising: means (102) for injecting an auxiliary flow (104) of a gas, configured to vary the orientation and/or speed of the auxiliary flow (104); suction means (106) for drawing in at least part of the injected auxiliary flow (112); and an internal auxiliary flow (109) return area (108) in one or more walls (110), said area being configured to allow the circulation of said part of the injected auxiliary flow (104) and the drawn-in auxiliary flow (112).</p> |
