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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 Verification of 2D Fitting Results 5.5 Comparison of 2D Stagnation Pressure Loss and Blade Channel Area Distribution Another way of comparing the same blade profile belonging to three different coordinate sources is to look at the stagnation pressure loss coefficient. The stagnation pressure loss coefficient is a measure of the loss in stagnation pressure across the blade profile due to viscous effect. As the simulations were carried out without any rotation of the mesh, this implies that no work is added to the fluid and hence the total enthalpy is constant across the profile. However, the fluid experiences a total pressure drop due to viscous effect. This behaviour is similar to the case of a stator blade. An illustration of the thermodynamic process is presented in figure 5.57. Figure 5.57: Enthalpy-Entropy diagram of a Stator Blade The stagnation pressure loss coefficient can be defined using equation 2.45b. This is re-presented in equation 5.20. δloss = P01,rel − P02,rel (5.20) P01,rel − P2 Using equation 5.20, the stagnation pressure loss coefficient is computed for all the profiles. In order to ensure a fair comparison between the different profile types, a fixed location on the inlet and outlet simulation domain was used to compute the mass averaged quantities. A comparison of the stagnation pressure loss coefficient of each profile belonging to the different coordinate sources is presented in table 5.9. Table 5.9: Comparison of Stagnation Pressure Loss Coefficient between different profile types Profile Type 2D fitted Actual Point Surface fitted 1865 1565 1265 2265 0.08112 0.14034 0.29563 0.04628 0.08629 0.13098 0.29418 0.04729 0.09055 0.13957 0.31320 0.04564 61

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