Aerodynamic Analysis of NACA 2412 Airfoil on UAV Aircraft Wing Using Ansys Fluent Software

Muhammad Robby; Arwizet Karudin; Refdinal; Yolli Fernanda

doi:10.24036/ijimce.v1i3.49

Authors

Muhammad Robby Departement Mechanical Engineering, Universitas Negeri Padang, INDONESIA
Arwizet Karudin Departement Mechanical Engineering, Universitas Negeri Padang, INDONESIA
Refdinal Departement Mechanical Engineering, Universitas Negeri Padang, INDONESIA
Yolli Fernanda Departement Mechanical Engineering, Universitas Negeri Padang, INDONESIA

DOI:

https://doi.org/10.24036/ijimce.v1i3.49

Keywords:

Aerodynamics, Airfoil, NACA 2412, UAV Wing, ANSYS, CFD

Abstract

Technological advances in the era of globalization have increased the demand for unmanned aerial vehicles (UAVs) for various applications, including environmental monitoring, weather research, agriculture, and military needs. The aerodynamic performance of UAVs is highly dependent on wing design, especially airfoils, which play an important role in generating lift and minimizing drag. This research analyzes the aerodynamic performance of the NACA 2412 airfoil on the UAV wing using Computational Fluid Dynamics (CFD) simulation through ANSYS Fluent software. The simulation was conducted with variations in angle of attack and speed to understand the pressure distribution, airflow pattern, and lift (Cl) and drag (Cd) coefficients. The results showed that the optimal angle of attack for the highest Cl/Cd ratio, at 10 m/s and 20 m/s, was 4°, which provided the best aerodynamic efficiency. However, increasing the angle of attack to 20° causes a significant decrease in the Cl/Cd ratio as the drag force increases faster than the lift force, posing a risk of aerodynamic instability. These findings make a significant contribution to designing more efficient and stable UAV wings, supporting the development of more reliable and optimized UAV technologies in the future.

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