Method for profiling a replacement blade as a replacement part for an old blade for an axial-flow turbomachine, characterized by the steps: - acquisition of the hub contour geometry and casing contour geometry of the flow duct of the old blade and also the axial position of the center of gravity of the airfoil of the old blade which is tension-mounted on one side of the hub or casing and/or of the maximum utilizable axial construction space of the old blade; - design of the geometry of the airfoil of the replacement blade, the tension-mounting-side section (5, 6) of the airfoil of the replacement blade lying essentially at the same location as the tension-mounting-side section (5, 6) of the airfoil of the old blade, and the airfoil of the replacement blade being inclined at its leading edge upstream with respect to the tension mounting with a view to optimizing the stage efficiency, with the result that the airfoil has a rearward sweep; - definition of a tension-mounting-near region of the airfoil of the replacement blade, in which region the positive influence of the rearward sweep upon the stage efficiency is classified as low; - axial displacement of the airfoil portion, arranged outside the region, of the replacement blade upstream until the axial position of the center of gravity of the airfoil of the replacement blade coincides essentially with the axial position of the center of gravity of the airfoil of the old blade and/or the mechanical integrity of the replacement blade is achieved, utilizing the maximum utilizable axial construction space of the old blade, the leading edge being inclined downstream with respect to the tension mounting in the region from the tension-mounting-side section of the airfoil of the replacement blade as far as the displaced airfoil portion of the replacement blade, with the result that the airfoil has a transition sweep in this region. - acquisition of the hub contour geometry and casing contour geometry of the flow duct of the old blade and also the axial position of the center of gravity of the airfoil of the old blade which is tension-mounted on one side of the hub or casing and/or of the maximum utilizable axial construction space of the old blade; - design of the geometry of the airfoil of the replacement blade, the tension-mounting-side section (5, 6) of the airfoil of the replacement blade lying essentially at the same location as the tension-mounting-side section (5, 6) of the airfoil of the old blade, and the airfoil of the replacement blade being inclined at its leading edge upstream with respect to the tension mounting with a view to optimizing the stage efficiency, with the result that the airfoil has a rearward sweep; - definition of a tension-mounting-near region of the airfoil of the replacement blade, in which region the positive influence of the rearward sweep upon the stage efficiency is classified as low; - axial displacement of the airfoil portion, arranged outside the region, of the replacement blade upstream until the axial position of the center of gravity of the airfoil of the replacement blade coincides essentially with the axial position of the center of gravity of the airfoil of the old blade and/or the mechanical integrity of the replacement blade is achieved, utilizing the maximum utilizable axial construction space of the old blade,