Variable contour nacelle assembly for a gas turbine engine

A gas turbine engine, comprising:

• a compressor section, a combustor section, and a turbine section;
• a nacelle assembly at least partially surrounding at least one of said compressor section, said combustor section and said turbine section, wherein said nacelle assembly includes an inlet lip section and a cowl section that each include an adjustable contour, each of said inlet lip section and said cowl section including a first surface that faces radially inward and a second surface that faces radially outward, each of said first surfaces and said second surfaces being moveable to influence said adjustable contours;
• and
• a controller that identifies an abnormal aircraft operating condition, wherein said controller selectively moves said inlet lip section and said cowl section of said nacelle assembly in response to detecting said abnormal aircraft operating condition.