A method of manufacturing an aerodynamic element with a trailing edge, the method comprising: casting the aerodynamic element with an initial, as-cast condition; wherein an initial shape of the trailing edge with the as-cast condition is generally squared-off with an expectation that the squared-off portion will be machined into a final edge-shape, and wherein the aerodynamic element with the as-cast condition is formed to define a discharge cavity through which coolant is discharged from the aerodynamic element during operations thereof, and the discharge cavity is at least initially mis-aligned with an expected position of the trailing edge in the final edge-shape; cooling the aerodynamic element; generating a predefined number of data points, wherein the generating of the predefined number of data points comprises one or more of scanning, probing and measuring the aerodynamic element with the as-cast condition, wherein the predefined number of data points are sufficient to characterize a position, size and shape of the aerodynamic element with the as-cast condition, and wherein the predefined number of data points are sufficient to characterize contours of the trailing edge relative to the position, the size and the shape of the aerodynamic element with the as-cast condition; comparing the data points to a nominal condition of the aerodynamic element to derive transformation parameters applicable to cutting toolpaths to adapt the cutting toolpaths toward correcting the as-cast condition, wherein when the aerodynamic element has the nominal condition, the discharge cavity is aligned with the expected position of the trailing edge in the final edge-shape; and driving a cutting machine in accordance with the adapted cutting toolpaths. casting the aerodynamic element with an initial, as-cast condition; wherein an initial shape of the trailing edge with the as-cast condition is generally squared-off with an expectation that the squared-off portion will be machined into a final edge-shape, and wherein the aerodynamic element with the as-cast condition is formed to define a discharge cavity through which coolant is discharged from the aerodynamic element during operations thereof, and the discharge cavity is at least initially mis-aligned with an expected position of the trailing edge in the final edge-shape; wherein an initial shape of the trailing edge with the as-cast condition is generally squared-off with an expectation that the squared-off portion will be machined into a final edge-shape, and wherein the aerodynamic element with the as-cast condition is formed to define a discharge cavity through which coolant is discharged from the aerodynamic element during operations thereof, and the discharge cavity is at least initially mis-aligned with an expected position of the trailing edge in the final edge-shape; cooling the aerodynamic element; generating a predefined number of data points, wherein the generating of the predefined number of data points comprises one or more of scanning, probing and measuring the aerodynamic element with the as-cast condition, wherein the predefined number of data points are sufficient to characterize a position, size and shape of the aerodynamic element with the as-cast condition, and wherein the predefined number of data points are sufficient to characterize contours of the trailing edge relative to the position, the size and the shape of the aerodynamic element with the as-cast condition; wherein the generating of the predefined number of data points comprises one or more of scanning, probing and measuring the aerodynamic element with the as-cast condition, wherein the predefined number of data points are sufficient to characterize a position, size and shape of the aerodynamic element with the as-cast condition, and wherein the predefined number of data points are sufficient to characterize contours of the trailing edge relative to the position, the size and the shape of the aerodynamic element with the as-cast condition; comparing the data points to a nominal condition of the aerodynamic element to derive transformation parameters applicable to cutting toolpaths to adapt the cutting toolpaths toward correcting the as-cast condition, wherein when the aerodynamic element has the nominal condition, the discharge cavity is aligned with the expected position of the trailing edge in the final edge-shape; and driving a cutting machine in accordance with the adapted cutting toolpaths. wherein when the aerodynamic element has the nominal condition, the discharge cavity is aligned with the expected position of the trailing edge in the final edge-shape; and driving a cutting machine in accordance with the adapted cutting toolpaths.