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 For the second test case, a comparison was made between the ’2d fitted’ and ’surface fitted’ pro- file. This is illustrated in figure 5.13 and 5.14 respectively. Figure 5.13: Comparison of 1865 Mach Contour Figure 5.14: Comparison of 1865 Pressure Contour between 2D fitted and Surface fitted Profile between 2D fitted and Surface fitted Profile It can be seen that the results are very similar for both profile although there are minor differences in the position of the shockwaves. Comparing figure 5.11 and 5.13, it can be concluded that the results of the 2d fitted profile matches more closely to the actual point profile than the surface fitted profile. For the third test case, a comparison was made between the actual point profile and the surface fitted profile. This is illustrated in figure 5.15 and 5.16. Figure 5.15: Comparison of 1865 Mach Contour between Surface fitted Profile and Actual point profile Figure 5.16: Comparison of 1865 Press. Contour between Surf. fitted Profile and Actual point profile For this test case, the pressure and mach contour of the actual point and surface fitted profile are very similar, making it comparable to the first test case. A comparison of the blade loading of all the different test cases will reveal their similarity and differences more closely. A comparison of the various blade loading in figure 5.17, 5.18 and 5.19 reveals that the actual point profile and the surface fitted profile actually have the closest fit. The kinks present in the various 50

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