Gas turbine engine with variable area fan nozzle

A nacelle assembly for a gas turbine engine comprising:

• a core nacelle defined about an engine centerline axis of rotation;
• a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path;
• a variable area nozzle in communication with said fan bypass flow path, said variable area nozzle having a first fan nacelle section and a second fan nacelle section, said second fan nacelle section axially movable relative said first fan nacelle section to define an auxiliary port to vary a fan nozzle exit area and adjust fan bypass airflow, said second fan nacelle section includes a leading edge region that defines a concave external contour that extends away from the engine centerline axis and said first fan nacelle section includes a trailing edge region that defines a convex internal contour that extends towards the engine centerline axis;
• and
• a flexible surface mounted to at least one of an inner surface at said convex internal contour and an outer surface at said concave external contour.