Electronic Theses and Dissertation

Penelitian ini bertujuan untuk menganalisis pengaruh variasi leading edge sweep angle terhadap karakteristik aerodinamika sayap pesawat tanpa awak (uav) jenis twin-boom fixed-wing menggunakan pendekatan simulasi computational fluid dynamics (cfd). model airfoil yang digunakan adalah naca 4412 dengan variasi sweep angle sebesar 0°, 5°, dan 11°. simulasi dilakukan menggunakan perangkat lunak ansys fluent 2024 r2 dengan model turbulensi reynolds-averaged navier-stokes (rans) tipe k–ε standard pada kondisi steady-state dan kecepatan jelajah 18 m/s pada ketinggian 140 mdpl. parameter yang dianalisis meliputi coefficient of lift (cl), coefficient of drag (cd), coefficient of pressure (cp), serta rasio efisiensi aerodinamika (cl/cd). hasil simulasi menunjukkan bahwa variasi sweep angle berpengaruh signifikan terhadap performa aerodinamika sayap. pada sweep angle 0°, nilai rasio cl/cd maksimum sebesar 15,6 diperoleh pada angle of attack (aoa) 4°. konfigurasi sweep angle 5° memberikan performa terbaik dengan nilai cl/cd maksimum sebesar 20,81 pada aoa 4°, menandakan efisiensi aerodinamika tertinggi. sedangkan pada sweep angle 11°, aliran menunjukkan kestabilan lebih baik pada aoa rendah dengan cl/cd mencapai 20,86 pada aoa 6°, namun mulai menurun pada aoa tinggi akibat fenomena separasi bertahap. dengan demikian, konfigurasi sweep angle 5° direkomendasikan sebagai desain optimal untuk meningkatkan efisiensi aerodinamika dan kestabilan penerbangan uav jenis twin-boom fixed-wing, terutama untuk misi pemetaan dan survei udara jarak menengah. kata kunci: uav twin-boom, sweep angle, cfd simulation, naca 4412, aerodinamika, ansys fluent

This study aims to analyze the effect of variations in the leading-edge sweep angle on the aerodynamic characteristics of a twin-boom fixed-wing unmanned aerial vehiCle (UAV) using the Computational Fluid Dynamics (CFD) simulation approach. The airfoil model employed is NACA 4412, with sweep angle variations of 0°, 5°, and 10.97°. Simulations were conducted using ANSYS Fluent 2024 R2 with the Reynolds-Averaged Navier–Stokes (RANS) turbulence model of the standard k–ε type under steady-state conditions and a cruise velocity of 18 m/s at an altitude of 140 meters above sea level. The analyzed parameters inClude the coefficient of lift (Cl), coefficient of drag (Cd), coefficient of pressure (Cp), and the aerodynamic efficiency ratio (Cl/Cd). The simulation results indicate that variations in sweep angle have a significant effect on the aerodynamic performance of the wing. At a sweep angle of 0°, the maximum Cl/Cd ratio of 15.6 was achieved at an angle of attack (AoA) of 4°. The 5° sweep angle configuration demonstrated the best performance, with a maximum Cl/Cd ratio of 20.81 at an AoA of 4°, indicating the highest aerodynamic efficiency. Meanwhile, at a 10.97° sweep angle, the airflow exhibited improved stability at low AoA, achieving a Cl/Cd ratio of 20.86 at an AoA of 6°, but the efficiency decreased at higher AoA due to progressive flow separation. Therefore, the 5° sweep angle configuration is recommended as the optimal design to enhance aerodynamic efficiency and flight stability of twin-boom fixed-wing UAVs, particularly for medium-range mapping and aerial survey missions. Keywords: Twin-boom UAV, Sweep Angle, CFD Simulation, NACA 4412, Aerodynamics, ANSYS Fluent.