A gas turbine engine comprises a gear train defined along an engine axis. A spool along the engine axis drives the gear train, and includes a low stage count downstream turbine. A fan rotates at a fan speed about the engine axis and drives the downstream turbine through the gear train. The fan speed is less than a speed of the downstream turbine. A core is surrounded by a core housing defined about the engine axis. A fan nacelle is mounted around the core nacelle to define a fan bypass airflow path for a fan bypass airflow. A bypass ratio defined by the fan bypass passage airflow divided by airflow through the core is greater than about ten (10).