Nacelle short inlet for fan blade removal

A gas turbine engine, comprising:

• a turbine;
• and
• a fan assembly operably connected to the turbine including:
• a fan including a plurality of fan blades, each fan blade extending radially outwardly from a fan hub to a blade tip, the plurality of blade tips defining a fan diameter;
• a nacelle surrounding the fan and defining a fan inlet upstream of the fan, relative to an airflow direction into the fan, the nacelle having a forwardmost edge defining an inlet length from the forwardmost edge to a leading edge of a fan blade of the plurality of fan blades, a ratio of inlet length to fan diameter between 0.20 and 0.45;
• and
• a nacelle inner surface defining a nacelle flowpath, the nacelle flowpath having a convex throat portion and a diffusion portion between the throat portion and the leading edge of the fan blade at a topmost portion of the nacelle, the throat portion having a minimum throat radius measured from a fan central axis greater than a blade tip radius measured relative to the fan central axis.