A fan stage for a gas turbine engine defining axial, radial and circumferential directions comprising: a hub; and a plurality of fan blades extending radially form the hub, wherein each fan blade comprises: an aerofoil portion having a leading edge extending from a root to a tip, the radial distance between the leading edge at the root and the leading edge at the tip defining a blade span characterized in that, when viewed along a circumferential direction: the angle (α) formed between the radial direction and a straight line drawn between the leading edge at the root and at the tip is in the range of from -6°and - 0.2°; and the angle (α (P1, P2)) formed between the radial direction and a line drawn between any two points (P1, P2) on the leading edge that have a difference in radius of at least 5% of the blade span is in the range of from -6°and 0°, where a negative angle indicates that the respective line has an axial component that is in the same direction as the axial component of the direction from a trailing edge to the leading edge of the blade; and wherein: when viewed along a circumferential direction, the maximum perpendicular distance (e) between any point on the leading edge and a straight line drawn between the leading edge at the root and at the tip is 5% of the blade span. a hub; and a plurality of fan blades extending radially form the hub, wherein each fan blade comprises: an aerofoil portion having a leading edge extending from a root to a tip, the radial distance between the leading edge at the root and the leading edge at the tip defining a blade span characterized in that, when viewed along a circumferential direction: the angle (α) formed between the radial direction and a straight line drawn between the leading edge at the root and at the tip is in the range of from -6°and - 0.2°; and the angle (α (P1, P2)) formed between the radial direction and a line drawn between any two points (P1, P2) on the leading edge that have a difference in radius of at least 5% of the blade span is in the range of from -6°and 0°, where a negative angle indicates that the respective line has an axial component that is in the same direction as the axial component of the direction from a trailing edge to the leading edge of the blade; and wherein: when viewed along a circumferential direction, the maximum perpendicular distance (e) between any point on the leading edge and a straight line drawn between the leading edge at the root and at the tip is 5% of the blade span. the angle (α) formed between the radial direction and a straight line drawn between the leading edge at the root and at the tip is in the range of from -6°and - 0.2°; and the angle (α (P1, P2)) formed between the radial direction and a line drawn between any two points (P1, P2) on the leading edge that have a difference in radius of at least 5% of the blade span is in the range of from -6°and 0°, where a negative angle indicates that the respective line has an axial component that is in the same direction as the axial component of the direction from a trailing edge to the leading edge of the blade; and wherein: when viewed along a circumferential direction, the maximum perpendicular distance (e) between any point on the leading edge and a straight line drawn between the leading edge at the root and at the tip is 5% of the blade span.