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Master Thesis Report Verification of 2D Fitting Results 5|Verification of 2D Fitting Results In this chapter, the report will focus on the verification of the 2D fitting approach that was used to reconstruct the rotor. In order to do so, the first part of this chapter will look into the methodology used to obtain the correct boundary conditions. After that, the second part of this report will focus on the mesh topology and analysis of the 2D results. 5.1 2D Inlet Boundary Conditions The 2D boundary conditions were derived based on information provided by the NASA Technical report 2879 [16]. A summary of the key information regarding the design and geometry data of the NASA Rotor 67 can be found in table 5.1. Table 5.1: Design and Geometry Data Parameters Design Rotation Speed Inlet Tip Relative Mach No. Mass Flow Hub to Tip Ratio Tip Radius No. of Rotor Blade Values Units 16043 rpm 1.38 - 33.25 kg/s 0.375 - 0.257 m 22 - Other than using the above information, the static pressure, temperature and density were assumed to be at ambient condition. Also, the air is considered to be an ideal gas. Table 5.2: Atmospheric Data Parameters Pressure Temperature Density γair Values 101325 288.15 1.225 1.4 Units Pascal K kg/m3 - The calculation procedure for the boundary conditions can be split into both inlet and outlet condition respectively. The inlet boundary condition was first calculated assuming a free vortex design rule. This imply that the absolute axial velocity along the span will be constant and that the free vortex constant is equal to the product of the absolute tangential velocity and the radius. Using the information provided in table 5.1, the hub radius can be computed as follows: Rhub = Rhub ∗ Rtip (5.1) Rtip 38PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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