Gas turbine engine inlet

A gas turbine engine comprising:

• a fan section including a fan rotatable about an engine longitudinal axis, the fan including a plurality of fan blades;
• a fan nacelle surrounding the fan and including an inlet, the inlet including an inlet leading edge plane and a throat aft of the inlet leading edge plane in an axial direction relative to the engine longitudinal axis;
• a core nacelle, and wherein the fan nacelle and the core nacelle establish a bypass flow path;
• a compressor section arranged in the core nacelle, the compressor section including a first compressor and a second compressor;
• a turbine section arranged in the core nacelle, the turbine section including a fan drive turbine and a second turbine;
• a fan hub mounting the fan and a spinner, and the spinner mounted forward of the fan in the axial direction;
• a geared architecture, and wherein the fan drive turbine drives the fan through the geared architecture;
• wherein the fan includes a fan leading edge forward-most point spaced apart from the inlet leading edge plane by an inlet length in the axial direction;
• wherein the spinner includes a spinner length from a spinner forward-most point to the fan leading edge forward-most point in the axial direction;
• wherein a ratio of the spinner length to the inlet length is greater than or equal to 0.5;
• wherein a fan pressure ratio is less than or equal to 1.45 measured across the plurality of fan blades alone at cruise at 0.8 Mach and 35,000 feet;
• and
• wherein a ratio of the inlet length to a diameter of the fan is less than or equal to 0.4.