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Master Thesis Report 3D Flow Simulation of the NASA Rotor 67 7.3.1 Simulation Setup The following parameters were considered for the simulation setup. Firstly, a steady state simulation is being considered. The rotation speed specified is based on the design rotation speed of 16043 rpm. The actual direction of the rotation speed is determined from the relative inflow angle (derived from the rotor blade geometry) as well as the specified absolute inflow angle. As for the inlet and outlet boundary condition, the total and static pressure were specified respectively. At the hub of the blade domain, a no slip wall boundary condition where the velocity of the fluid at the wall boundary is set to zero is specified. CFX by default considers that the wall is rotating with the grid and hence they are moving with respect to the stationary reference frame. For the case of a fan rotor without casing, a no slip wall with zero rotation velocity will be specified at the tip of the blade domain. In the case of a fan rotor with casing, the casing wall is stationary in the non rotating reference frame and therefore a counter rotating velocity, −ωR is specified at the tip wall boundary. In this simulation, the case of a rotor with and without casing was considered. For the uniform inflow boundary condition, the inlet total pressure is specified based on the radial averaged total pressure found from the outlet plane of the finalized inlet configuration. As for the non uniform inflow boundary condition, the values were specified based on the circumferential averaged total pressure values found for each radial position (See figure 7.11). In order to apply the circumfer- ential averaged pressure value found at each radial position onto the actual scale of the NASA Rotor 67, the radial values of both the inlet configuration and the rotor blade was normalized before the total pressure values found at the outlet the inlet configuration can be applied across the span of the rotor blade inlet. The two main turbulence model available in ANSYS CFX is the k-epsilon and SST model. The k-epsilon turbulence model uses a scalable wall function for near wall treatment. The main advantage of the scalable wall functions is that they can be applied on arbitrary fine meshes. In the case that the boundary layer is not fully resolved, CFX relies on the logarithmic wall func- tion approximation to model the boundary layer without affecting the validity of the scalable wall function approach. In the case that detailed investigation of the boundary layer is required, the SST turbulence model is used in conjunction with the automatic near-wall treatment to take advantage of the additional effect in the viscous sublayer. For this simulation, the SST turbulence model is being considered. For the solver control settings, a residual target of 1e-7 as well as a maximum of 500 iterations is specified for each test run. This is necessary in order to ensure convergence of the various residuals. 7.3.2 Mesh Convergence Studies In order to ensure that the finalized mesh density does not influence the accuracy of the simulation results, meshes of varying density were created and simulated. The mass averaged pressure change across the inlet and outlet face of the rotor was compared for all the mesh densities created. The chosen mesh density should ensure convergence in the results of the chosen simulation parameter while keeping the computational cost to a minimal. Due to the limit imposed on the allowable minimum discretized mesh size by SALOME, the setting which gives the densest mesh and provides the converged solution was chosen. A mesh with a total of 686328 elements and 131847 nodes was finally chosen for this simulation. 80PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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