A blade (10, 410) for a rotor of a wind turbine having a substantially horizontal rotor shaft, the rotor comprising a hub, from which the blade (10, 410) extends substantially in a radial direction when mounted to the hub, the blade (10, 410) comprising: - a profiled contour comprising a pressure side and a suction side as well as a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge, the profiled contour generating a lift when being impacted by an incident airflow, - the profiled contour in the radial direction being divided into a root region (30, 130, 230, 330, 430) with a substantially circular or elliptical profile closest to the hub, an airfoil region (34, 134, 234, 334, 434) with a lift generating profile furthest away from the hub, and preferably a transition region (32, 132, 232, 332, 432) between the root region (30, 130, 230, 330, 430) and the airfoil region (34, 134, 234, 334, 434), the transition region (32, 132, 232, 332, 432) having a profile gradually changing in the radial direction from the circular or elliptical profile of the root region (30, 130, 230, 330, 430) to the lift generating profile of the airfoil region (34, 134, 234, 334, 434), wherein - the airfoil region (34, 134, 234, 334, 434) comprises at least a first longitudinal segment extending along at least 20% of a longitudinal extent of the airfoil region (34, 134, 234, 334, 434), the first longitudinal segment (140, 240, 340) comprising a first base part (141, 241, 341, 441) having a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge, characterised in that - the first base part (141, 241, 341, 441) has an inner dimension that varies linearly in the radial direction of the blade (10, 410) in such a way that an axial induction factor of the first base part (141, 241, 341, 441) without flow altering devices at a rotor design point deviates from a target axial induction factor, and wherein - the first longitudinal segment (140, 240, 340) is provided with a number of first flow altering devices arranged so as to adjust the aerodynamic properties of the first longitudinal segment (140, 240, 340) to substantially meet the target axial induction factor at the design point, and wherein - the airfoil region (34, 134, 234, 334, 434) comprises a plurality of longitudinal segments (140, 240, 340; 242; 342) each having a base part (241, 341, 441, 243, 343, 443) having a separately linearly varying dependency in the radial direction of the blade (10, 410) and a number of flow altering devices. - a profiled contour comprising a pressure side and a suction side as well as a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge, the profiled contour generating a lift when being impacted by an incident airflow, - the profiled contour in the radial direction being divided into a root region (30, 130, 230, 330, 430) with a substantially circular or elliptical profile closest to the hub, an airfoil region (34, 134, 234, 334, 434) with a lift generating profile furthest away from the hub, and preferably a transition region (32, 132, 232, 332, 432) between the root region (30, 130, 230, 330, 430) and the airfoil region (34, 134, 234, 334, 434), the transition region (32, 132, 232, 332, 432) having a profile gradually changing in the radial direction from the circular or elliptical profile of the root region (30, 130, 230, 330, 430) to the lift generating profile of the airfoil region (34, 134, 234, 334, 434), wherein - the airfoil region (34, 134, 234, 334, 434) comprises at least a first longitudinal segment extending along at least 20% of a longitudinal extent of the airfoil region (34, 134, 234, 334, 434), the first longitudinal segment (140, 240, 340) comprising a first base part (141, 241, 341, 441) having a leading edge and a trailing edge with a chord extending between the leading edge and the trailing edge, characterised in that - the first base part (141, 241, 341, 441) has an inner dimension that varies linearly in the radial direction of the blade (10, 410) in such a way that an axial induction factor of the first base part (141, 241, 341, 441) without flow altering devices at a rotor design point deviates from a target axial induction factor, and wherein - the first longitudinal segment (140, 240, 340) is provided with a number of first flow altering devices arranged so as to adjust the aerodynamic properties of the first longitudinal segment (140, 240, 340) to substantially meet the target axial induction factor at the design point, and wherein - the airfoil region (34, 134, 234, 334, 434) comprises a plurality of longitudinal segments (140, 240, 340; 242; 342) each having a base part (241, 341, 441, 243, 343, 443) having a separately linearly varying dependency in the radial direction of the blade (10, 410) and a number of flow altering devices.