A fan assembly for a gas turbine engine (20) includes a fan (42) including a plurality of fan blades (92). Each fan blade extends radially outwardly from a fan hub to a blade tip (94). The plurality of blade tips define a fan diameter (D). A nacelle (80) surrounds the fan (42) and defines a fan inlet upstream of the fan (42), relative to an airflow direction into the fan (42). The nacelle (80) has 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 (92). A ratio of inlet length to fan diameter (D) is between 0.20 and 0.45. A nacelle (80) inner surface defines a nacelle flowpath. The nacelle flowpath has a convex throat portion (122) and a concave diffusion portion (126) between the throat portion and the leading edge of the fan blade at a bottommost portion of the nacelle (80).