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Master Thesis Report Parameterisation and Reconstruction of the NASA Rotor 67 X Figure 4.3: Sliced 2D Profiles of the NASA Rotor 67 4.2 Step 2: Fitting the camberline of the 2D Profiles After extracting the profiles from the CGNS mesh, the next step is to fit the individual 2d profiles. This process begins with fitting the camberline of each 2d profile. The camberline fitting process is a mix of automatic and manual work. The goal is to first use the interface of the blade modeller to fit the 2d profiles and then to later develop a geometry fitting algorithm which extracts information from the discretized points and refit the camberline based on the extracted information. Using the ’plane cutting’ feature of tecplot, each of the 2d slices are discretized into many points along the contour of the profile. Before they can be imported into the blade modeller (BM), an import and export function/interface for the discretized 2d points was developed for the BM. After the points were imported, a separate script was developed in such a way that the user is able to interactively select the point closest to the leading and trailing edge of these points for the formation of the initial camberline. As previously mentioned, the camberline is defined by the leading edge position, axial chord length the stagger angle as well as the blade metal angle at the inlet and outlet of the profile (See figure 2.13). From the selected leading and trailing edge position of the discretized points, the BM would then recalculate the axial chord length and stagger angle respectively. The blade inlet/outlet metal angle were then determined by the following approach in the script belonging to the class of the geometry fitting algorithm: • Calculate the tangent values of the points closest to the leading and trailing edge for both the suction and pressure side curve of the 2D profiles • Calculate the difference in tangent values between adjacent pair of points for both the suction and pressure side curve 29PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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