| 摘要 |
The invention relates to a nacelle (23) for a turbojet engine (21), comprising an air intake structure (25) capable of directing an air flow towards a fan (27) of a turbojet engine (21), a middle structure (29) for surrounding said fan (27) and to which the air intake structure (25) is secured so as to provide aerodynamic continuity, and a downstream section (31) to which the middle structure (29) is attached, characterised in that the air intake structure (25) is adapted so as to define a continuous extension of the walls (33; 34) of a flying wing (3) so that the air intake structure (25), the middle structure (29), and the downstream structure (31) are in aerodynamic continuity with the flying wing (3). The invention also relates to a flying wing (3) and to an aircraft (1) comprising such a nacelle. |
