An integrated propulsion system (10) comprises components that include a gas turbine engine (20) and a nacelle assembly (82). The nacelle assembly (82) includes a fan nacelle (86) arranged at least partially about a fan (42) and an engine. The system includes a fan section (22) at least partially defined by the fan nacelle (82), and the fan section (22) has a fan pressure ratio of less than about 1.7. The engine includes a turbine section (28) configured to drive the fan section (22) and a compressor section (24), the compressor section (24) including a first compressor (44) and a second compressor (52). An overall pressure ratio is provided by the combination of a pressure ratio across the first compressor (44) and a pressure ratio across the second compressor (52), and wherein the overall pressure ratio is greater than or equal to about 35. The fan section (22) is configured to deliver a portion of air into the compressor section (24), and a portion of air into a bypass duct, and wherein a bypass ratio, defined as a volume of air passing to the bypass duct compared to a volume of air passing into the compressor section (24), is equal to or greater than about 5.