Fan stagger angle for geared gas turbine engine

A propulsor blade comprising:

• an airfoil extending over a span between a root and a tip and having a chord between a leading edge and a trailing edge such that said chord forms a stagger angle α with regard to a rotational axis of said airfoil, and said stagger angle α is less than 62° at all positions along said span, with said hub being at 0% of said span and said tip being at 100% of said span.

A method for controlling propulsion losses in a gas turbine engine, the method comprising:

• establishing a design pressure ratio that is from 1.1 to 1.55 with regard to an inlet pressure and an outlet pressure of a bypass flow passage in which a propulsor of the gas turbine engine is located, the propulsor including a hub and a row of propulsor blades extending from the hub, each of the propulsor blades having a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge such that the chord forms a stagger angle α with a rotational axis of the propulsor;
• and
• in response to the design pressure ratio, establishing the stagger angle α to be less than 62° at all positions along the span, with the hub being at 0% of said span and the tip being at 100% of the span.