Patent ID: 7870722

Claim:
An aircraft system, comprising: an aircraft nozzle attachable to an aircraft turbofan engine, the nozzle including: a first flow path wall bounding a first flow path and being positioned to receive engine exhaust products; a second flow path wall bounding a second flow path and being positioned to receive engine bypass air, the first flow path wall being positioned between the first and second flow paths, the second flow path wall being positioned between the second flow path and an ambient air flow path; and multiple flow passages positioned in at least one of the first and second flow path walls, the flow passages being positioned to passively direct gas from a corresponding flow path within the flow path wall through the flow path wall to a corresponding flow path external to the flow path wall, neighboring flow passages having neighboring circumferentially extending and circumferentially spaced apart exit openings positioned at an interface with the corresponding flow path external to the flow path wall, wherein for individual flow passages, the flow passage is angled circumferentially by a greater amount toward a first neighboring flow passage with which it is paired in a first circumferential direction than toward a second neighboring flow passage in a second circumferential direction opposite the first circumferential direction.