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The technology of design and manufacture of Unmanned Aerial Vehicle (UAV), has been rapidly improved in the world. At present, the industry in which UAV are used is quite extensive. Take the military mission as an example, for the execution of short-range front-line reconnaissance missions and even long-range reconnaissance missions, it is necessary to have a carrier with excellent aerodynamic efficiency for the mission, regardless of whether the power system of the vehicle is equipped with an internal combustion engine or an electric brushless DC (BLDC) motor. Even the operational efficiency is high, the endurance limit of the UAV is still determined by the design of aerodynamic shape, especial for the un-matured development of current battery.
The major objectives of this thesis are to simulate the flow field of the BLDC power’s UAV, and solve its lift and drag. Then, modified the wing shape to see if the aerodynamic performance is better than the original design. At first, the execute procedures are using SolidWorks to construct the models, and applying ANSYS CFX to analyze the flow fields. Finally, the simulation results are validated using actual flight test data.
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