Analisis Aerodinamika Pada Sayap Pesawat Fixed Wing Untuk Pesawat Tanpa Awak Jenis Talon Menggunakan Software Berbasis Computational Fluid Dynamics

Abstract

UAV (unmanned aerial vehicle) is an unmanned aircraft that flies automatically with its autopilot system. Airplanes can fly because of the lift around the wings of the plane. Lift is generated from the design of the wing and the selection of the airfoil shape. To be able to perform optimally from the airfoil, it is necessary to do an aerodynamic analysis on the airfoil. Aerodynamic analysis on aircraft wings with clark y, naca 0012 and naca 2412 airfoil types. The purpose of this research is to analyze the effect of variations in the angle of attack of the airfoils 0°, 1°, 2°, 3°, 4°, 5° 6°. Against the lift coefficient (CL), drag coefficient (CD), lift (FL) and drag (FD) to obtain the design of the aircraft wing, affects the control surface of the angular influence when driven into fluid flow. The method used is Computational Fluid Dynamics (CFD). So that the lowest CL results were obtained on the airfoil naca 0012 angle of attack 0° with a value of 0.0081, the highest CL on the airfoil clark y angle of attack 6° with a value of 0.9199. While the lowest CD is on the naca 0012 airfoil with an angle of attack of 0° with a value of 0.0047, the highest CD is on a clark y airfoil with an angle of attack of 6° with a value of 0.0390. For the lowest FL value, namely on the airfoil naca 0012, the angle of attack is 0° with a value of 4.3112 N, the highest FL is on the airfoil clark y, the angle of attack is 6° with a value of 489.6156 N. Meanwhile, the lowest FD value is on the airfoil naca 0012, the angle of attack is 0 ° with a value of 2.5015 N, the highest FD is the clark y airfoil with an angle of attack of 6° with a value of 20.7577 N. The highest CL/CD value of the three airfoils is naca 0012 37.8 with an angle of attack of 5°. The results of the control surface simulation are still effective up to an angle of 25°.