Patent ID: 8596573

Claim:
A method of altering air pressure on a surface of a nacelle assembly, the method comprising the steps of: (a) sensing an operable condition of an aircraft; (b) selecting between increasing local air pressure and decreasing local air pressure at the nacelle surface of the nacelle assembly through a plurality of holes on said nacelle surface based on the sensed operable condition; and (c) decreasing air flow at a first area of the nacelle surface and increasing airflow at a second area of the nacelle surface, the first area different from the second area, wherein the first area is radially outwards of the second area, wherein the second area of the nacelle surface defines a bypass flow passage of the nacelle assembly and the plurality of holes are in communication with a first interior volume of the nacelle and a second interior volume of the nacelle, the first interior volume and the second interior volume are separated by a wall.