Patent ID: 7048230

Claim:
A laminar flow nacelle for an aircraft engine, the nacelle having an outer member defining an aerodynamic shape for a fluid, the nacelle having an inner member defining a chamber with the outer member of the nacelle, the outer member of the nacelle having a porous region at a first region of the outer member, the porous region allowing a flow of fluid, free of any pump, into the chamber, at least one duct to connect the chamber to at least one aperture in the outer member at the second region of the outer member downstream of the first region, whereby in operation the static pressure at the first region being greater than the static pressure at a second region such that at least some of the boundary layer of the fluid flows through the porous region at the first region of the nacelle through the at least one duct to the at least one aperture at the second region with said duct being free of any obstruction.