Gas turbine engine inlet

A gas turbine engine comprising:

• propulsor means for providing propulsion, the propulsor means including a plurality of propulsor blades rotatable about an engine longitudinal axis,
• an inlet for providing airflow to the propulsor, the inlet including an inlet leading edge plane;
• reduction means for reducing a rotational speed of an output that drives the propulsor means relative to an input;
• first compression means for compressing airflow from the propulsor means;
• second compression means for compressing airflow from the first compression means;
• first expansion means for driving the second compression means in response to expanding airflow from the second compression means;
• second expansion means for driving the input of the reduction means in response to expanding airflow from the first expansion means;
• a hub mounting the propulsor blades and a spinner, and the spinner mounted forward of the propulsor blades in an axial direction relative to the engine longitudinal axis;
• wherein the propulsor means includes a propulsor 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 propulsor 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;
• and
• wherein a normalized internal area distribution is defined between the inlet leading edge plane and the propulsor leading edge forward-most point, and the normalized internal area distribution is monotonically convergent.