The present study is a conceptual design of a delta wing unmanned aerial vehicle (UAV) based on the requirements of its mission and then conducting a parameter study that can relate the changes in aerodynamic and geometric parameters to the UAV's performance. Regarding the characteristics of this manuscript, it can be mentioned that by having the results of a quantitative study in the field of geometry and aerodynamics, then it is possible to move towards optimization and reduction of construction costs. In addition, the aerodynamic of delta wing is considered and the modeling of delta wing is done using simple algebraic equations that presents lift and drag forces quantity generally. This UAV designed in such a dimension that 2 people can carry, initialize, guide and recover themselves. In addition, the maximum speed of 280 km/h is suggested during the flight. The minimum flight altitude of the present UAV while carrying out a mission is more than 2000 meters. The power required for flight increases with increasing flight speed but decreases with increasing altitude. Finally, the numerical study was performed using Ansys Fluent 19 software to investigate more parameters such as pressure and Mach number distributions around the present UAV
کلید واژگان :Statistical design, Numerical simulation, Unmanned aerial vehicle, Delta wing, Aerodynamic parameters.
ارزش ریالی : 600000 ریال
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