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.