A gas turbine engine comprising: a spool; a turbine coupled with said spool; a propulsor coupled to be rotated at a design speed about an axis by said turbine through said spool; and a gear assembly coupled between said propulsor and said spool such that rotation of said turbine drives said propulsor at a different speed than said spool, wherein: said propulsor includes a hub and a row of propulsor blades that extend from said hub, each of said propulsor blades includes an airfoil body that extends in a radial span between a root and a tip, in a chord direction between a leading edge and a trailing edge and in a thickness direction between a pressure side and a suction side; said gas turbine being characterised in that: said leading edge of the airfoil body has a swept profile such that, at the design speed, a component of a relative velocity vector of a working gas that is normal to the leading edge is subsonic along the entire radial span; said swept profile has a rearward sweep from 0% to at least 50%, of the span or radial span, and said swept profile has a forward sweep from at least 60% to 100% of said span or radial span, with said root being at 0% of said (radial) span and said tip being at 100% of said span or radial span; said rearward sweep has a sweep angle of less than 15°; said rearward sweep has a sweep angle that decreases from 0% to at least 50%, of said span or radial span; said rearward sweep has a sweep angle between 5° and 10° from 0% to 50%, of said span or radial span; said swept profile has a single, exclusive transition between a rearward sweep and a forward sweep from 0% to 100% of said span or radial span, said transition being between 55% and 60% of said span or radial span; and a percentage S REAR of said span or radial span is said rearward sweep and a percentage S FOR of the span or radial span is said forward sweep, and a ratio of S REAR / S FOR is between 1.25 and 1.30. a spool; a turbine coupled with said spool; a propulsor coupled to be rotated at a design speed about an axis by said turbine through said spool; and a gear assembly coupled between said propulsor and said spool such that rotation of said turbine drives said propulsor at a different speed than said spool, wherein: said propulsor includes a hub and a row of propulsor blades that extend from said hub, each of said propulsor blades includes an airfoil body that extends in a radial span between a root and a tip, in a chord direction between a leading edge and a trailing edge and in a thickness direction between a pressure side and a suction side; said gas turbine being characterised in that: said leading edge of the airfoil body has a swept profile such that, at the design speed, a component of a relative velocity vector of a working gas that is normal to the leading edge is subsonic along the entire radial span; said swept profile has a rearward sweep from 0% to at least 50%, of the span or radial span, and said swept profile has a forward sweep from at least 60% to 100% of said span or radial span, with said root being at 0% of said (radial) span and said tip being at 100% of said span or radial span; said rearward sweep has a sweep angle of less than 15°; said rearward sweep has a sweep angle that decreases from 0% to at least 50%, of said span or radial span; said rearward sweep has a sweep angle between 5° and 10° from 0% to 50%, of said span or radial span; said swept profile has a single, exclusive transition between a rearward sweep and a forward sweep from 0% to 100% of said span or radial span, said transition being between 55% and 60% of said span or radial span; and a percentage S REAR of said span or radial span is said rearward sweep and a percentage S FOR of the span or radial span is said forward sweep, and a ratio of S REAR / S FOR is between 1.25 and 1.30. said leading edge of the airfoil body has a swept profile such that, at the design speed, a component of a relative velocity vector of a working gas that is normal to the leading edge is subsonic along the entire radial span; said swept profile has a rearward sweep from 0% to at least 50%, of the span or radial span, and said swept profile has a forward sweep from at least 60% to 100% of said span or radial span, with said root being at 0% of said (radial) span and said tip being at 100% of said span or radial span; said rearward sweep has a sweep angle of less than 15°; said rearward sweep has a sweep angle that decreases from 0% to at least 50%, of said span or radial span; said rearward sweep has a sweep angle between 5° and 10° from 0% to 50%, of said span or radial span; said swept profile has a single, exclusive transition between a rearward sweep and a forward sweep from 0% to 100% of said span or radial span, said transition being between 55% and 60% of said span or radial span; and a percentage S REAR of said span or radial span is said rearward sweep and a percentage S FOR of the span or radial span is said forward sweep, and a ratio of S REAR / S FOR is between 1.25 and 1.30.