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Master Thesis Report 3D Flow Simulation of the NASA Rotor 67 7.4 3D Uniform and Non Uniform Inflow Simulation Results In this section of the chapter, the 3D results will be presented and discussed. In particular, the focus of the results will be on the performance comparison of the rotor under both uniform and non uniform inflow boundary condition as well as the visualisation of the blade to blade domain for the velocity vector, pressure as well as the entropy loss across the blade channel. Finally, the streamlines view of the meridional channel will also be presented. An illustration of the isometric view of the 3D blade assembly (22 blades) as well as the meridional view of a single blade is presented in figure 7.12 and 7.13. Figure 7.12: Isometric View of 3D Blade Assembly Figure 7.13: Meridional View of Single Blade 7.4.1 Blade Loading Comparison A comparison of the blade loading plot for the case of a uniform and non uniform inflow condition is presented in figure 7.14 to 7.19. For this comparison, the ducted fan configuration was used in the comparison of the results between the uniform and non uniform inflow condition. The blade loading at the 20%, 50% and 80% span are presented. Since non uniform inflow results in a change in the circumferential averaged total pressure at each radial position, a change in the inflow incidence angle is expected. The resulting effect is a change in the blade loading and the overall performance of the rotor in terms of efficiency and entropy loss. As the change in total pressure is more abrupt near the tip and hub section of the blade, greater differences in the blade loading at the 80% and 20% span position is expected. In figure 7.14, 7.15, 7.18 and 7.19, it can be seen that the blade loading plot at the 20% and 80% span position exhibits more differences as compared to the blade loading plot at the 50% span position. Also, it is noticeable that a larger change in the blade loading occur at the trailing edge pressure side of the blade. At the 20% span position, the shock (abrupt change in pressure) is shifted towards the trailing edge while it is shifted towards the leading edge at the 80% span position. Secondly, the strength of the shock also reduces as a result of the lower inlet total pressure for the non uniform boundary condition. 7.4.2 Comparison of the Blade to Blade Domain Visualization The visualization of the velocity vectors as well as the entropy change across the blade to blade domain is presented below. The plot of the velocity vector is illustrated in figure 7.20, 7.21, 7.22, 7.23, 7.24 81PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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