Laminar flow necelle

Details Laminar flow necelle Laminar flow necelle

1987-07-27

1989-01-24

Peters, Jr., Joseph F.

Aeronautics and astronautics

Aircraft structure

Details

244 53R, 244 35R, B64D 2900

Patent

active

047996331

ABSTRACT:
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 that 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 intersection 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.

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AIAA Paper No. 73-86 by Robert H. Liebeck, dated Jan. 10-12, 1973, "A Class of Airfoils Designed for High Lift in Incompressible Flow".

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