Nowadays, the aviation sector is facing the main problem that affects the planet, global warming, produced by high levels of pollution. This project aims to design an aircraft powered by electric energy. Moreover, the tasks this aircraft should accomplish are the ones it was an aerial taxi. Also, it is desired that can carry out other tasks types as rescue or health emergencies. Therefore, it is intended the aircraft should take-off and land vertically, appearing the term eVTOL (electric Vertical Take-Off and Landing). In addition to this, to improve cruise performance, the aircraft should have conventional wings. Starting with the design, it has been divided into 4 parts, being this project the one in charge of the design of the propulsion system, as well as the one for the design of carrying enough energy to be able to perform the objectives of this aircraft must accomplish. These design objectives are the mass of the aircraft (3200 kg), the cruise speed (200 mph), and the maximum range that should be achieved (1000 km). Furthermore, during this project it has been initiated the own design of a ducted fan, wanting it to be as maximum efficient as possible for the performance of the ONA eVTOL. Proceeding with the design process, the path that has been followed is starting with the necessary dimensions computation of the disk area required to produce enough thrust to take-off. With this, the peak power value could be found, which is important to know which engine the aircraft needs. Also, the power through all the trip phases has been computed, to compare this power requirement with the available stored energy. With this comparison, the maximum theoretical range of the aircraft could be found. Finally, for the own design of the ducted fan, it has been tested some design techniques in a CFD simulation to see if they are suitable to be applied to the design itself. The software used for this has been SolidWorks, in particular, its tool destined for CFD simulations ¿Flow Simulation¿. In this study, it has been tested the possibility of having more than one rotor in the fan, as well as different geometries of the duct to maximize the performance of the propeller for both take-off/landing and cruise phases.
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