Selection Of Airfoil For LSU-05 Aircraft Wing With Numerical Aerodynamic Analysis

Analysis with numerical method has been done for the selection of LSU-05 unmanned vehicle airfoil.The analysis process is done by comparing four airfoil’s performance at a certain reynolds number. The four airfoil shapes are compared by comparing the simulation result of their aerodynamical properties such as lift coefficient, drag coefficient, and the polar drag. The needs of the aircraft itself is to be able to carry a payload of 30 kg, range of 200 km, and endurance of 3 hours. The NACA 4415 airfoil is chosen because it meets the requirement for LSU-05.