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Master Thesis Report Verification of 2D Fitting Results The varying level of mesh discretization within the entire 2D domain is illustrated in figure 5.5, 5.6 and 5.7. It can be seen that the leading and trailing edge radial zone has a much denser mesh as compared to the zone around the blade wall. Also, the zone around the blade wall exhibits a denser mesh as compared to the region of the inflow, outflow, periodic 1 and periodic 2 zone. 5.3.2 SU2 CFD Solver Settings Once an appropriate mesh has been generated by UMG 2, the next step is to set up the right numer- ical/spatial integration scheme, turbulence model and boundary conditions for the configuration file of SU2. The menter shear stress transport (SST) turbulence model which is composed of a blend- ing of the k − ω and k − ε model is used for all the simulation run. Secondly, the inlet stagnation pressure/temperature and the outlet static pressure are based on the values provided in table 5.5. Thirdly, since a non rotating simulation is applied, the relative flow is used in order to account for the peripheral speed. This implies that the relative flow angle will be imposed on the inlet boundary condition and that the flow angle in the outlet plane is also in the relative frame of reference. For all the mesh generated, a periodic boundary condition is imposed on the top and bottom side of the blade to blade domain since it is assumed that the flow solution is periodic across the blade row for every pitch distance. This is a simplification of a real flow simulation since every blade within the blade row is different due to manufacturing uncertainties and that the blade row may be exposed to unsteady flow phenomenon. A brief description of the common numerical settings used for all the 2D simulation is presented below. The solver settings can be divided into 4 main categories; common parameters for numerical scheme, flow numerical methods, turbulent numerical methods as well as the convergence parameter. A list of the commonly considered parameters for the simulation run are presented in table 5.6, 5.7 and 5.8. Table 5.6: Common Parameters for Numerical Methods Parameters Numerical Method For Spatial Gradient CFL Number Number of Total Iterations Type Weighted Least Square 10 7500 Table 5.7: Flow Numerical Methods Parameters Convective Numerical Method Spatial Numerical Order Integration Slope Limiter Time Discretization Scheme Type Roe 2nd Order Limiter Venkatakrishnan Euler Implicit It should be pointed out that the total number of iterations required was finally decided based on the convergence of the density parameter as well as its order of magnitude reduction. Other than the use of the density parameter, other solutions exist for use as an convergence parameter. A plot of the density convergence results for one of the tested profile (1865) is presented in figure 5.8. 46PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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