Gas turbine engine with noise attenuating variable area fan nozzle

1. A method of reducing a total effective perceived noise level of a gas turbine engine with a variable area fan nozzle in communication with a fan bypass flow path, the variable area fan nozzle having a first fan nacelle section and a second fan nacelle section, the second fan nacelle section axially movable relative the first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust a fan bypass airflow comprising:

defining an airfoil leading edge region of the second fan nacelle section by an elliptical contour which defines a baseline configuration with a radius less than 0.05δ where δ represents an upstream boundary layer thickness;

increasing the semi-minor axis relative to the baseline configuration; and

rotating the elliptical contour to align tangentially to a suction surface of the airfoil leading edge region to increase an airfoil leading edge radius relative to a baseline configuration to reduce boundary layer turbulence ingestion leading edge noise.

2. The method as recited in claim 1 , further comprising:

maintaining the suction surface constant relative to the baseline configuration; and

altering a leading edge curvature of a pressure surface to define the increased airfoil leading edge radius.

3. The method as recited in claim 1 , further comprising:

defining the leading edge region along an approximately first quarter chord of the second fan nacelle section.

4. The method as recited in claim 1 , further comprising:

redefining a pressure surface, corresponding to the increase in semi minor axis, to align tangentially, to increase the airfoil leading edge radius relative to the baseline configuration of radius <0.05δ to reduce boundary layer turbulence ingestion leading edge noise.

5. The method as recited in claim 1 , wherein the leading edge radius is increased to 0.1δ to 0.5δ.