Abstract:
This report, provided by the Author, was written about the investigation of airfoil section for designing of Unmanned Aerial Vehicle (UAV). The analysis of airfoil for Unmanned Aerial Vehicle (UAV) has been reviewed based on the parameters of lift coefficient and drag coefficient. One of the important focuses in this phase is the determination of the airfoils shape. This report sole objective is to determine which airfoil that is best suited for the UAV, as well as presenting the airfoils characteristic properties, in comparison to other similarly airfoils. The design was performed using XFOIL code (an interactive program for the design and analysis of subsonic isolated airfoils). NACA2.5411, NACA2414 and NACA2415 were tested and analyzed by using XFOIL program. They were chosen as they have different thickness percentage. Those airfoils are then being tested in the wind tunnel to be compared and analyze with the XFOIL simulation. Angle of attack of 2.5 has been used in the wind tunnel test and tested with speed from 5m/s until 30m/s with increment of 5m/s. From the XFOIL program, NACA 2414 met the minimum requirement for the design of UAV wing as it produced high lift compared to other tested airfoils. The project can be said as semi-successful as the wind tunnel is not calibrated and resulting a different reading from the conceptual data.
