Fan blade for a turbofan gas turbine engine

A fan (12) for a turbofan gas turbine engine comprises a rotor hub (36) and a plurality of radially extending fan blades (20) integral with the hub (36) to form an integrally bladed rotor. Each fan blade (20) defines a leading edge (34). A hub radius (R HUB ) is the radius of the leading edge (34) at the hub (36) relative to a centerline of the fan. A tip radius (R TIP ) is the radius of the leading edge (34) at a tip (40) of the fan blade (20) relative to the centerline of the fan. The ratio of the hub radius to the tip radius (R HUB /R TIP ) is at least less than 0.29. In a particular embodiment, this ratio is between 0.25 and 0.29. In another particular embodiment, this ratio is less than or equal to 0.25.