Gas turbine engine having slim-line nacelle

1. A nacelle assembly for a gas turbine engine, comprising:

a nacelle defined about an axis and having an inlet lip section and an inlet internal diffuser section;

a variable area fan nozzle positioned adjacent an aftmost segment of said nacelle, said variable area fan nozzle being moveable between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than said first discharge airflow area;

at least one sensor that detects a windmilling condition of said gas turbine engine; and

a controller in communication with said at least one sensor, wherein said controller moves said variable area fan nozzle from said first position to said second position in response to the detection of said windmilling condition.

2. The nacelle assembly as recited in claim 1 , further comprising a core cowl at least partially within a fan cowl of said nacelle, wherein said first discharge airflow area and said second discharge airflow area are defined between an inner surface of said fan cowl and an outer surface of said core cowl.

3. The nacelle assembly as recited in claim 1 , further comprising a first boundary layer control device positioned near said inlet lip section, wherein said first boundary layer control device is actuated by said controller in response to detection of at least one operability condition.

4. The nacelle assembly as recited in claim 3 , further comprising a second boundary layer control device positioned downstream of said first boundary layer control device and near said inlet internal diffuser section, wherein said second boundary layer control device is actuated by said controller in response to detection of said at least one operability condition.

5. The nacelle assembly as recited in claim 4 , wherein said variable area fan nozzle is moved to said second position simultaneously with the actuation of said first boundary layer control device and said second boundary layer control device in response to detection of said at least one operability condition, wherein said at least one operability condition includes at least one of a static condition, a cross-wind condition and a high angle of attack condition.

6. A gas turbine engine system, comprising:

a nacelle defined about an axis and having an inlet lip section and an inlet internal diffuser section, wherein said nacelle includes a variable area fan nozzle moveable to influence a discharge airflow area of said nacelle;

a core cowl at least partially within a fan cowl of said nacelle;

at least one boundary layer control device positioned near at least one of said inlet lip section and said inlet internal diffuser section;

a turbofan positioned within said nacelle;

at least one compressor and at least one turbine positioned downstream of said turbofan;

at least one combustor positioned between said at least one compressor and said at least one turbine;

at least one sensor that produces a signal representing a windmilling condition; and

a controller that receives said signal, wherein said controller selectively moves said variable area fan nozzle in response to receiving said signal.

7. The system as recited in claim 6 , wherein said variable area fan nozzle includes at least one flap assembly, said at least one flap assembly moveable between a first position having a first discharge airflow area and a second position having a second discharge airflow area greater than said first discharge airflow area.

8. The system as recited in claim 7 , comprising an actuator assembly in communication with said controller and operable to move said at least one flap assembly between said first position and said second position.

9. The system as recited in claim 6 , wherein said at least one boundary layer control device includes a first boundary layer control device and a second boundary layer control device, said first boundary layer control device positioned near said inlet lip section and said second boundary layer control device positioned near said inlet internal diffuser section, wherein said inlet internal diffuser section is downstream from said inlet lip section.

10. The system as recited in claim 9 , wherein said first boundary layer control device and said second boundary layer control device are actuated by said controller in response to detection of an operability condition, wherein the actuation of said first boundary layer control device and said second boundary layer control device includes at least one of injection of airflow within said nacelle and suction of airflow within said nacelle.

11. The system as recited in claim 10 , wherein said operability condition includes at least one of a static condition, a cross-wind condition, and a high angle of attack condition.

12. The system as recited in claim 10 , wherein said variable area fan nozzle is moveable simultaneously with the actuation of said first boundary layer control device and said second boundary layer control device in response to detection of said operability condition.

13. The system as recited in claim 6 , wherein said variable area fan nozzle is positioned near an aftmost segment of said nacelle.

14. The system as recited in claim 6 , wherein said windmilling condition comprises an engine out condition during flight subsequent to take-off.