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Master Thesis Report Parameterisation and Reconstruction of the NASA Rotor 67 between the reconstructed and actual rotor. This is because only a straight slice of the face closest to the tip section can be executed during the geometry extraction process. There could also be minor differences in the curvature of the blade leading and trailing edge although this is difficult to inspect visually. A comparison of their 3D results will be demostrated in the later part of this thesis. 4.6 Design Trend of the NASA Rotor 67 By using the BM to reconstruct the rotor, the complete design information of the rotor can be extracted and analysed. A discussion of their general design trend will be presented in this section. In figure 4.16, the angle distribution of the NASA Rotor 67 is being presented. NASA Rotor 67 Design Data Beta In Distribution Beta Out Distribution Stagger Distribution Beta Out - Beta In 100 50 0 −50 0.0 0.2 0.4 0.6 0.8 1.0 Normalized Span Figure 4.16: Angle Distribution of NASA Rotor 67 The following trend can be observed. Firstly, it can be seen that the stagger angle increases towards the tip. This is done mainly to allow for maximum stagger angle at the tip. Maximum stagger angle at the tip allows for a lower blade loading and tip losses [15]. In the ASME paper written by Yong Sang Yoon, Seung Jin Song and Hyoun Woo Shin [15], it was found that the pressure rise across the rotor blade reduces as the stagger angle increases. A reduction in the pressure rise across the blade implies a reduction in the blade loading. The other general trend is that the angular value of βout − βin decreases towards the tip while the radial value increases toward the tip. The is done mainly to keep the enthalpy change and consequently the blade loading across the rotor to be constant. The other important aspect is the thickness distribution of the rotor. It can be seen that the overall thickness of the rotor decreases from hub to tip for both the suction and pressure side. Also, the 35 Angle Distribution [◦ ]PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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