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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 Literature Review Figure 2.17: Influence of arctangent stretching parameter on points distribution along ā€™uā€™ parameter [7] Figure 2.18: Construction of Blade Profile Suc- tion/Pressure Side [7] construction of a B-Spline surface along the span-wise direction. Within the blade modeller, the blade can be either stacked through the center of gravity of the mid control profile or through the leading edge of each control profile. During the generation of the B spline surfaces for the suction/pressure side as well as the LE/TE circular arc surfaces, the total number of control points along each control profile as well as the degree of all the spanwise B-Spline curves has to be kept constant. Some other examples of blade stacking can be found in the paper of Tom Verstraete [8]. In his paper, the stacking process of an axial turbine is being demonstrated. This is illustrated in figure 2.19 Figure 2.19: Stacking of a 3D Axial Turbine Blade [8] The rotor blade profiles are stacked via its center of gravity while the vanes are stacked through its trailing edge points. The straight stacked shape is then altered by applying a lean or sweep distri- bution to several intermediate profiles between the hub and shroud. The lean and sweep law can be defined using beizer curves for which the control points are the optimization parameters [8]. In other cases, the lean and sweep law can also be defined by angle and distance parameters so that a straight forward relation between the lean/sweep parameters and performance parameters can be obtained. 18

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