Nacelle drag reduction device for a turbofan gas turbine engine

Details Nacelle drag reduction device for a turbofan gas turbine engine Nacelle drag reduction device for a turbofan gas turbine engine

2006-11-17

2009-10-20

Eldred, J. Woodrow (Department: 3641)

Aeronautics and astronautics

Aircraft structure

Details

C244S05300R, C244S204000, C060S226100, C060S262000

Reexamination Certificate

active

07604201

ABSTRACT:
The nacelle drag reduction device comprises a substantially circular and axis symmetrical external airfoil concentric with a aft section of the nacelle and located outside a propulsive jet zone defined behind the engine when operating, the airfoil being positioned at a location providing a maximum streamline angle with reference to the main axis of the engine and a highest streamline curvature.

REFERENCES:
patent: 3568790 (1971-03-01), Sankey
patent: 4228652 (1980-10-01), Short
patent: 4410150 (1983-10-01), Lahti
patent: 4466587 (1984-08-01), Dusa et al.
patent: 4696159 (1987-09-01), Horgan
patent: 4799633 (1989-01-01), Lahti et al.
patent: 2005/0011993 (2005-01-01), Konings
International Search Report, PCT/CA2007/001812, Jan. 17, 2008.

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