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Master Thesis Report Literature Review Brief Description of Modelling Equations in SU2 Several form of the Reynold Average Navier Stokes (RANS) equation have been implemented in SU2. They include the compressible, incompressible, Arbitrary Lagrangian-Eulerian,etc. As a subset of the RANS equation, both the laminar Navier Stokes as well as the inviscid Euler equations are also available by disabling turbulence modelling and removing viscosity respectively. In the case of turbu- lence modelling, both the Spalart-Allmaras (S-A) model as well as the Menter Shear Stress Transport (SST) model have been implemented. The Menter SST turbulence model is a two equation model that blends the traditional k − ω and k − ε model. For the modelling of laminar to turbulence transition, the γ − Reθt transition model which is an adaptation of the model of Langtry and Menter [14] have been implemented. This model is an correlation based model that augments the Spalart-Allmaras turbulence model with two equations. For simulations that involve steady rotation of aerodynamic bodies, it is advantageous to transform the system of flow equation into a reference frame (a.k.a ro- tating frame) that rotates with the body of interest [13]. As such, a flow field that is unsteady when viewed from the inertial frame can be solved in a steady manner without the need for grid motion. This is achieved by applying a transformation of the RANS equation from the inertial reference frame to the rotating frame. In the case that the rotation of the aerodynamic bodies includes unsteady flow phenomenon, solutions which includes grid motion is necessary. Therefore, the Arbitrary Lagrangian- Eulerian (ALE) formulation is also implemented in SU2. For wave related equations, both the Ffowcs Williams - Hawking (FW-H) equation and the linear elasticity equation was implemented for aeroacoustic and linear elastic small deformation problems respectively. Other physical models such as the heat equation, Gauss’s law as well as the plasma equation have also been implemented in SU2. The Gauss law is part of the Maxwell equations and is used to relate the distribution of electric charge to the resulting electric field [13]. The plasma flow equation is tightly coupled with the gauss law for the calculation of electric field generated by any local separation of charge[13]. In the context of this research, the compressible/incompressible RANS equation as well as the Menter SST turbulence model have been mainly used for the 2D and 3D simulations. 25PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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