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Master Thesis Report Literature Review 2|Literature Review In this chapter, a review of the most relevant literature is summarised and presented. The aim of this chapter will be to provide the reader a brief introduction of concepts that will be used throughout this entire report. The first sub-section of this chapter will touch on propulsion airframe integration. The second sub-section will present a cycle analysis on the effect of boundary layer ingestion on the thermodynamic and propulsive efficiency. The third sub-section of this report will focus on blade parametrisation , construction, loss mechanism as well as the performance characterisation of the rotor blade. Finally, the last sub-section of this chapter will touch on the capabilities and function of SU2 (Stanford University Unstructured), a CFD tool that was used throughout this research work. 2.1 Propulsion Airframe Integration (PAI) Propulsion airframe integration (PAI) is an important element to consider when meeting modern aviation requirement of reduced emissions, noise and fuel consumption. In the case of the Blended Wing Body concept, PAI can be achieved by either podding the engines onto the aft fuselage or embedding the engine into the fuselage. Figure 2.2: BWB with embedded engines Figure 2.1: BWB with podded engines An illustration of both concept is shown in figure 2.1 and 2.2 above. Fundamentally, the podded engine concept allows a clean undisturbed airflow into the engine which provides a high total pressure recovery and low inlet distortion. Secondly, the podded engine concept is a well understood and proven installation technique that can be implemented easily. The main disadvantage of such a concept is the increased wetted area which means an increase in the profile drag. The use of pylon also implies additional structural weight which can reduce the overall fuel efficiency of the aircraft. The presence of unshielded inlet design also leads to larger noise pollution comparatively. Lastly, the higher thrust line of the podded engine concept implies a larger horizontal control surface needed for trimming the flight. 4PDF Image | Aerodynamic Design of the NASA Rotor 67 for Non Uniform Inflow
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