9. A method of designing a gas turbine engine comprising:
providing a core nacelle defined about an engine centerline axis;
providing a fan nacelle mounted at least partially around said core nacelle to define a fan bypass flow path for a fan bypass airflow;
providing a gear train within said core nacelle;
providing a first spool along said engine centerline axis within said core nacelle to drive said gear train, said first spool includes a first turbine section including between three¡Vsix (3¡V6) stages, and a first compressor section;
providing a second spool along said engine centerline axis within said core nacelle, said second spool includes a second turbine section including at least two (2) stages and a second compressor section;
providing a fan including a plurality of fan blades to be driven through the gear train by the first spool, wherein the bypass flow path is configured to provide a bypass ratio of airflow through the bypass flow path divided by airflow through the core nacelle that is greater than about six (6) during engine operation.