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Master Thesis Report Verification of 2D Fitting Results As seen from figure 5.9 and 5.10, a different length of the inlet domain may result in a different inlet boundary condition as a result of the spurious reflection caused by downstream potential effect. This effect is more pronounced for the Mach number as compared to the static pressure. As such, the simulation domain which has an inflow/outflow domain length of 150% of the axial chord is used for the remaining simulation. 5.4.2 Comparison of Different Coordinate Sources for Profile 1865 In this subsection, the simulation results of profile 1865 belonging to three different coordinate sources will be compared. As mentioned in chapter 4, the distributed points of each control profile was first extracted from the CGNS mesh that was provided. After that, a geometry fitting algorithm was de- veloped to fit the BSpline curve of the pressure/suction side to the distributed points along the blade profile contour. Finally, a BSpline surface was generated to fit across all the control profiles on both the pressure and suction side of the blade. Hence, each blade profile can originate from 3 different coordinate sources depending on the stage of the construction process. The profile generated directly from the distributed points of the original CGNS mesh will be known as ’actual point profile’. The profile generated from the fitting of the BSpline curve using the geometry fitting algorithm will be known as the ’2D fitted profile’. Finally, the profile generated from the slice of the 3D blade belonging to the BSpline surfaces will be known as the ’surface fitted profile’. The comparison of the blade profiles will be made based on results from the Mach and Pressure contour distribution. For the first test case, a comparison was made between the ’actual point’ profile and the ’2D fitted’ profile. This is illustrated in figure 5.11 and 5.12. Figure 5.11: Comparison of 1865 Mach Contour Figure 5.12: Comparison of 1865 Pressure Contour between 2D fitted and Actual Point Profile between 2D fitted and Actual Point Profile In figure 5.11, the thick lines emanating from the surface of the blade contour represents the generation of a shockwave as the flow velocity exceeds Mach 1. A visual comparison of the shockwave position between both profile types shows that the overall shape of both profile is very similar although there are slight differences in the trailing edge wake pattern and the exact position of each shockwave. In the case that both profiles have exactly the same shape, the periodicity of the solution from both profiles will be preserved. This implies that the pressure and mach contour pattern of both profile will be exactly the same. 49PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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