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 3D Flow Simulation of the NASA Rotor 67 18000 16000 14000 12000 10000 8000 6000 4000 2000 Plot of Total Pressure versus Angular Position 0 0 50 100 150 200 250 300 350 400 Angular Position [◦ ] R = 0.7 R = 0.8 R = 0.9 R = 1.0 R = 1.1 R = 1.2 R = 1.3 R = 1.4 R = 1.5 R = 1.55 R = 1.6 Figure 7.8: Plot of total pressure versus angular position for varying radial position 300 250 200 150 100 50 Plot of Velocity versus Angular Position 0 0 50 100 150 200 250 300 350 400 Angular Position [◦ ] R = 0.7 R = 0.8 R = 0.9 R = 1.0 R = 1.1 R = 1.2 R = 1.3 R = 1.4 R = 1.5 R = 1.55 R = 1.6 Figure 7.9: Plot of velocity versus angular position for varying radial position the circumferential distortion intensity, the mid radius was used as a reference radius for comparison with other inlet configuration. The calculation procedures are based on equations 2.52, 2.53, 2.54, 2.55 presented in chapter 2. The results are illustrated in figure 7.10. 77 Velocity [m/s] Total Pressure [Pascal]

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