| 摘要 |
<p>A boundary layer control system in an aircraft comprises a outflow opening (20) arranged in a skin section (18) of the aircraft, which outflow opening (20) provides a suction force when air flows along the skin section (18), at least one duct couplable (14, 16) with the outflow opening (20) and coupled to an boundary layer control component (10) and an air control device (22). The air control device (22) is adapted for selectively providing air from a pressurized air source to the at least one duct (14, 16) for purging a perforation of the boundary layer control component (10) or inducing the suction of air through the boundary layer control component (10) to the outflow opening (20). Especially, bleed air from an APU in a tail region of the aircraft may be used for purging the boundary layer control component (10).</p> |
