A method of manufacturing a wind turbine blade by using the design of a longitudinal segment of a first wind turbine blade for the design of a second wind turbine blade, wherein the first wind turbine blade and the second wind turbine blade each comprise a longitudinally extending base part having: - 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 with a substantially circular or elliptical profile closest to the hub, an airfoil region with a lift generating profile furthest away from the hub, and preferably a transition region between the root region and the airfoil region, the transition region having a profile gradually changing in the radial direction from the circular or elliptical profile of the root region to the lift generating profile of the airfoil region, characterised in that the method comprises the steps of: a) taking a first blade design of a first base part of a first longitudinal segment of the airfoil region of a first blade, b) using the first blade design for the first base part on a first longitudinal segment of the airfoil region of a second blade, so that an axial induction factor of the first base part on the second blade without flow altering devices at a rotor design point deviates from a target axial induction factor, and c) providing the first longitudinal segment of the second blade with first flow altering devices (446'; 448') so as to adjust the aerodynamic properties of the first longitudinal segment and obtain the correct lift and drag coefficients at the given angle of attack to substantially meet the target axial induction factor at the design point on the second blade, wherein the first longitudinal segment extends along at least 20% of a longitudinal extent of the airfoil region of the second blade, wherein the first longitudinal segment of the first blade is located in a first radial distance from a root end of the first blade, and wherein the first longitudinal segment of the second blade is located in a second radial distance from a root end of the second blade, and wherein the first radial distance is different from the second radial distance. - 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 with a substantially circular or elliptical profile closest to the hub, an airfoil region with a lift generating profile furthest away from the hub, and preferably a transition region between the root region and the airfoil region, the transition region having a profile gradually changing in the radial direction from the circular or elliptical profile of the root region to the lift generating profile of the airfoil region, characterised in that the method comprises the steps of: a) taking a first blade design of a first base part of a first longitudinal segment of the airfoil region of a first blade, b) using the first blade design for the first base part on a first longitudinal segment of the airfoil region of a second blade, so that an axial induction factor of the first base part on the second blade without flow altering devices at a rotor design point deviates from a target axial induction factor, and c) providing the first longitudinal segment of the second blade with first flow altering devices (446'; 448') so as to adjust the aerodynamic properties of the first longitudinal segment and obtain the correct lift and drag coefficients at the given angle of attack to substantially meet the target axial induction factor at the design point on the second blade, wherein a) taking a first blade design of a first base part of a first longitudinal segment of the airfoil region of a first blade, b) using the first blade design for the first base part on a first longitudinal segment of the airfoil region of a second blade, so that an axial induction factor of the first base part on the second blade without flow altering devices at a rotor design point deviates from a target axial induction factor, and c) providing the first longitudinal segment of the second blade with first flow altering devices (446'; 448') so as to adjust the aerodynamic properties of the first longitudinal segment and obtain the correct lift and drag coefficients at the given angle of attack to substantially meet the target axial induction factor at the design point on the second blade, wherein