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Master Thesis Report Literature Review 1 360 (Pav)i = 360 0 n=N 1 P(θ)idθ = N ∗ dθ P(θ)idθ (2.54) n=1 1 θ2,i (Pav,low)i = (θ ) ̄ i θ1,i N dθ i N1dθ N is the total number of sampling points taken over a 360◦ sector and dθ is the angular size of each sampling point. 1 2 P(θ)idθ = (θ ) ̄ P(θ)idθ (2.55) N1 is the starting index position where the total pressure falls below the (Pav)i and N2 is the index position where the total pressure rises above the (Pav)i value. A low total pressure region occurs when the local total pressure P(θ)i lies below the ring average total pressure, Pav,i. If two low total pressure regions occur within 25◦ of each other, it is treated as a single once-per-revolution low total pressure region. If two low total pressure regions are separated by more than 25◦, the circumferential distortion intensity is taken to be the maximum of the two. An illustration of the various definitions presented above is shown in figure 2.24. Figure 2.24: Definitions for Pav and Pav,low 2.4 Capabilities and Function of SU2 In this section, a brief introduction on the capabilities and function of the Stanford University Un- structured (SU2) CFD Code will be described. This is a tool that was used throughout this research work. SU2 is a computational analysis and design software that is being developed to solve complex multi-physics analysis and optimization task using arbitrary unstructured meshes. Fundamentally, it is able to discretize and solve problems described by Partial Differential Equation (PDE) as well as PDE constrained optimization problems such as optimal shape design. Multidisciplinary problem usually involves the interaction of several separate software module that represent different physical models. In order to avoid integration problems and the loss of efficiency, having a common set of numerical solutions algorithms and code architecture is beneficial [13]. There- fore, the ability to integrate multiphysics models, parameterize the system as well as to optimise the system is critical. For the purpose of optimization, it is necessary to obtain the gradient of the re- sponse to variation with respect to a large number of design parameters. As such, SU2 is in-built 23PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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