Patent ID: 8839805

Claim:
A nacelle for a gas turbine engine system, comprising: a housing having a pressure side and a suction side, wherein the pressure side is radially outward of the suction side; and a passage extending between the pressure side and the suction side for permitting airflow from the pressure side to the suction side, wherein the passage includes a first curved section having an inlet at the pressure side, a linear section connected with the first curved section, and a second curved section connected with the linear section and having an outlet at the suction side, wherein the outlet has a cross sectional area smaller than a cross sectional area of the linear section, and a first portion of the housing, on the pressure side, forward of the inlet, defining a tangential plane, and a second portion of the housing, on the pressure side, aft of the inlet, is spaced radially outward from the tangential plane.