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A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar air

A gas turbine engine system includes a nacelle having a pressure side and a suction side. A passage extends between the pressure side and the suction side that permits airflow from the pressure side to the suction side. The passage receives turbulent airflow over the nacelle to produce a laminar airflow over the nacelle aft of the passage to thereby reduce drag on the nacelle.

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1. A nacelle for a gas turbine engine system, comprising: a housing having a pressure side and a suction side; anda passage extending between the pressure side and the suction side for permitting airflow from the pressure side to the suction side and the passage includes a first curved section havin

1. A nacelle for a gas turbine engine system, comprising: a housing having a pressure side and a suction side; anda passage extending between the pressure side and the suction side for permitting airflow from the pressure side to the suction side and the passage includes a first curved section having an inlet at the pressure side, a linear section connected with the first curved section, and a second curved section connected with the linear section and having an outlet at the suction side, the outlet having a cross sectional area smaller than a cross sectional area of the linear section, wherein the passage is configured for passively drawing turbulent airflow into the nacelle; wherein the pressure side is located radially outward from the suction side and the passage is located upstream of a fan. 2. The nacelle as recited in claim 1, wherein the passage includes a section having a progressively increasing cross-sectional area. 3. The nacelle as recited in claim 2, wherein the section having a progressively increasing cross sectional area extends between the passage inlet at the pressure side and the linear section of the passage. 4. The nacelle as recited in claim 3, wherein the section having a progressively increasing cross sectional area includes a first cross-sectional area at the passage inlet and a second cross-sectional area at the linear section that is about 2.5 times greater than the first cross-sectional area. 5. The nacelle as recited in claim 1, wherein the first curved section has a progressively increasing cross-sectional area. 6. The nacelle as recited in claim 1, wherein the housing includes an airflow surface and the passage inlet extends through the airflow surface, the airflow surface having a first section forward of the inlet relative to a direction of the airflow and a second section aft of the inlet, the first section defining a tangential plane wherein the second section is spaced apart from the tangential plane. 7. The nacelle as recited in claim 6, wherein the second section is spaced an offset distance of about 0.25 inches from the tangential plane. 8. The nacelle as recited in claim 1, wherein the housing includes an airflow surface having a section where airflow transitions from a first airflow that is generally laminar to a second airflow having a turbulent airflow component, wherein the passage extends from the airflow surface aft of the transition section. 9. The nacelle as recited in claim 6, wherein the second section defines a scoop configured to direct airflow into the passage. 10. The nacelle as recited in claim 8, wherein the turbulent airflow is caused by one of debris or airflow distortion from high angle of attack. 11. A gas turbine engine system comprising: a fan for air intake;a compressor for compressing the air;a combustor for burning fuel in the presence of the air to produce an expanding gas stream;a turbine driven by the expanding gas stream to drive the fan and the compressor;a nacelle that extends about the fan, the compressor, the combustor, and the turbine, the nacelle having a forward section that includes an outside airflow surface and an inside airflow surface relative to the fan; anda passage located upstream of a fan extending between an inlet on the outside airflow surface and an outlet on the inside airflow surface, a first curved section extends from the inlet, a linear section connected with the first curved section, a second curved section connected with the linear section, the outlet includes a cross sectional area smaller than a cross sectional area of the linear section, the passage configured to permit airflow from the outside airflow surface toward the inside airflow surface, wherein the passage is configured for passively drawing turbulent airflow into the nacelle. 12. The system as recited in claim 11, wherein the passage includes a section having a progressively increasing cross-sectional area extending between the passage inlet at the outside airflow surface and the linear section of the passage. 13. The system as recited in claim 12, wherein the section having a progressively increasing cross-sectional area includes a first cross-sectional area at the passage inlet and a second cross-sectional area at the linear section that is about 2.5 times greater than the first cross-sectional area. 14. The system as recited in claim 11, wherein the passage inlet extends through the outside airflow surface, the outside airflow surface including a first section forward of the inlet relative to an airflow direction over the outside airflow surface and a second section aft of the inlet, the first section defining a tangential plane wherein the second section is spaced apart from the tangential plane. 15. The system as recited in claim 11, wherein the passage includes the inlet located forward of the outlet and the inlet and the outlet are located forward of the fan. 16. A method of controlling a turbulent airflow over an airflow surface of a nacelle, comprising: diverting at least a portion of the turbulent airflow from the airflow surface into a continuous passage located upstream of a fan extending between an inlet on a radially outer side of the nacelle and an outlet on a radially inner side of the nacelle to produce a generally laminar airflow over the airflow surface, the passage includes a first curved section extends from the inlet, a linear section connected with the first curved section, and a second curved section connected with the linear section, wherein the outlet has a cross sectional area smaller than a cross sectional area of the linear section. 17. The method as recited in claim 16, further including producing a pressure differential between the passage inlet at the airflow surface and the passage outlet to urge the turbulent airflow into the passage. 18. The method as recited in claim 16, further including diffusing the turbulent airflow to reduce a speed of the turbulent airflow within the passage. 19. The method of claim 16, wherein the airflow surface is radially outward of the passage. 20. The method of claim 16, further including directing at least a portion of the turbulent airflow through on outlet on a second airflow surface of the nacelle. 21. The method of claim 17, wherein the pressure differential is provided passively such that an additional component is not used. 22. A nacelle for a gas turbine engine system, comprising: a housing having a pressure side and a suction side; anda passage extending between the pressure side and the suction side for permitting airflow from the pressure side to the suction side, wherein the passage is configured for passively drawing turbulent airflow into the nacelle, wherein the housing includes an airflow surface and the passage includes an inlet that extends through the airflow surface, the airflow surface having a first section forward of the inlet relative to a direction of the airflow and a second section aft of the inlet, the first section defining a tangential plane wherein the second section is spaced apart from the tangential plane and wherein the second section is spaced an offset distance depending on a thickness of an expected turbulent boundary layer.