| 摘要 |
Improved nacelle for an aircraft engine which permits the aerodynamic drag to be reduced during flight. In one of the embodiments, the nacelle encloses a jet engine and comprises a leading edge 34 and a trailing edge 36, between which extends a reference chord 38, and an outer surface 40 which is continuous between the leading edge and the trailing edge. The outer surface 40 comprises a front part 42, an intermediate part 44, and a rear part 46, and exhibits a profile defined by a variable width measured orthogonally between the chord and the outer surface. This profile has a maximum thickness at the intersection 48 of the front and intermediate parts, which is situated at most about 36% of the length of the chord from the front edge, and makes it possible to increase the extent of the laminar flow over the nacelle in such a way as to reduce the aerodynamic drag. Application to aircraft engines. <IMAGE>
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