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Master Thesis Report 3D Flow Simulation of the NASA Rotor 67 7|3D Flow Simulation of the NASA Ro- tor 67 In this chapter, the results from the 3D simulation of the NASA Rotor 67 will be analysed and discussed. In particular, the 3D flow simulation of the rotor under uniform and non uniform inflow condition as well as the flow simulation of the rotor with and without casing will be compared. The first section of this chapter will present on the boundary conditions which were obtained from literature and the information extracted from it. The second section of this chapter will discuss about the development of the actual 3D non uniform boundary condition. The non uniform boundary condition was basically produced by quantifying the circumferential averaged total pressure at each normalized radial position and then applying them onto the same normalized position of the rotor blade. The actual 3D uniform inlet boundary condition was then produced by using the radial averaged total pressure. The outlet static pressure was then quantified based on the total to static pressure ratio found from [16]. The third section of this report will then present on the simulation settings used in ANSYS CFX. The fourth section of this chapter will compare the simulation results between a uniform and non uniform inflow condition. Finally, the fifth section of this chapter will compare the simulation results of a rotor blade under uniform inflow inlet condition with and without a casing. The case of a simulation with and without casing was considered since it was necessary to understand the effect of using either a non slip boundary condition or a non slip boundary condition with counter rotating radial velocity setting for the shroud wall in ANSYS CFX. 7.1 3D Uniform Inflow Boundary Conditions In this section, the uniform inflow boundary conditions extracted from the NASA Technical Report TP2879 [16] are illustrated in figure 7.1, 7.2 and 7.3 71PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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