F - Mech Eng,Light,Heat,Weapons – 02 – K
Patent
F - Mech Eng,Light,Heat,Weapons
02
K
60/93
F02K 1/00 (2006.01) B64D 29/00 (2006.01) B64D 33/02 (2006.01)
Patent
CA 1209354
LAMINAR FLOW NACELLE ABSTRACT OF THE DISCLOSURE An improved nacelle is provided for housing an aircraft engine and reducing aerodynamic drag during aircraft operation. In one embodiment, the nacelle houses a gas turbine engine and comprises a leading edge and a trailing edge, having a reference chord extending therebetween, and an outer surface which is continuous from the leading edge to the trailing edge. The outer surface includes a forward portion, an intermediate portion and an aft portion and has a profile defined by a varying thickness measured perpendicularly from the chord to the outer surface. The profile has a maximum thickness at the intersection of the forward and intermediate portions, which inter- section is located greater than about 36% of the chord from the leading edge, and is effective for increasing laminar flow over the nacelle for reducing aerodynamic drag.
438631
Lahti Daniel J.
Younghans James L.
Company General Electric
Eckersley Raymond A.
LandOfFree
Laminar flow nacelle does not yet have a rating. At this time, there are no reviews or comments for this patent.
If you have personal experience with Laminar flow nacelle, we encourage you to share that experience with our LandOfFree.com community. Your opinion is very important and Laminar flow nacelle will most certainly appreciate the feedback.
Profile ID: LFCA-PAI-O-1232042