Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow

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Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow ( aerodynamic-design-nasa-rotor-67-non-uniform-inflow )

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Master Thesis Report Verification of 2D Fitting Results It can be seen that the mach and pressure contour patterns are very similar for both profile types. The position of their shocks almost coincide and the trailing edge wake pattern is identical. A closer examination of their blade loading will reveal more information about their similarity and differences. For the second test case, a comparison was made between the 2d fitted and surface fitted profile. Figure 5.25: Comparison of 1265 Mach Contour Figure 5.26: Comparison of 1265 Pressure Contour between 2D fitted and Surface fitted Profile between 2D fitted and Surface fitted Profile It can be seen that the 2d fitted and surface fitted profiles are different in the sense that the position of their shocks are shifted with respect to each other. However, both profile types have almost identical trailing edge wake pattern. For the third test case, a comparison is made between the actual point and surface fitted profile. Figure 5.27: Comparison of 1265 Mach Contour Figure 5.28: Comparison of 1265 Pressure Contour between Actual point and Surface fitted Profile between Actual point and Surface fitted Profile It can be seen that the actual point and surface fitted profiles are different in the sense that the position of their shocks are shifted with respect to each other. However, both profile types have almost identical trailing edge wake pattern. This suggest that the blade loading would be similar except for a shift in the kink which represents the shockwave. A comparison of the blade loading and profile geometry for the different profile types are shown in figure 5.29, 5.30 and 5.31. 53

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