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Master Thesis Report Research Goals and Objectives 3.2 Motivation From the literature study that was conducted, it was found that there exists a large number of de- velopment in various aspect of BLI for a BWB. Most of the literature that were found focuses on the system benefit of BLI. A small number of papers looked specifically into the inlet design for a em- bedded engine configuration. As compared to the podded engine configuration, it was found that the embedded engine configuration can provide an overall reduction in fuel consumption due to reduced momentum deficit. However, the benefits of BLI have shown to be very sensitive to the magnitude of the fan and duct losses. Therefore, the design of ingestion tolerant fan is critical in achieving increased fuel efficiency. Secondly, few literature exists that investigate the flow phenomenon on the rotor blade and on the parametric design of ingestion tolerant fan blades for embedded engines configurations on a BWB. Therefore, the main goal of this thesis is to investigate the flow physics and performance of the rotor under non uniform inflow condition and then to propose possible design improvement for the fan blade so as to minimise entropy loss. 3.3 Scope The scope of this thesis is to focus on the continued development of an in-house blade modeller which is subsequently used to parameterize and reconstruct the NASA Rotor 67. After the re-construction of the NASA Rotor, the other aspect of this thesis is to focus on the coupling and development of meshing templates for 2D/3D geometries based on an open source meshing software, SALOME. Thereafter, the next part of this thesis will focus on the development of a mesh writer that prints SU2 Mesh file format based on extracted information from SALOME. When the necessary mesh files have been generated, the final aspect of this thesis will focus on the simulation and analysis of various blade geometries. Taking into consideration the total time frame of this project, the scope of this thesis will not include the development of an optimization algorithm for the blade modeller. 27PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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