CFD-Based Numerical Analysis of Aerodynamic Performance for Different NACA Airfoils
DOI:
https://doi.org/10.38032/jea.2026.02.005Keywords:
Airfoil, Angle of Attack, Aerodynamic Performance, NACA, Computational Fluid Dynamics (CFD)Abstract
Aeronautical engineering relies critically on the optimization of aerodynamic airfoil shapes, the precise configuration of which significantly influences aircraft efficiency. Consequently, comprehensive research aimed at improving these designs is essential for advancing aerospace innovation. In this study, computational fluid dynamics (CFD) is employed to numerically analyze the flow behavior over distinct NACA airfoil profiles under various angles of attack, encompassing both low‑speed and high‑speed regimes. The primary objective is to identify viable pathways for enhancing wing‑section aerodynamics. Initial analysis confirms that the angle of attack exerts a substantial influence on the lift‑to‑drag ratio, establishing it as a key performance metric. The validity of the numerical methodology is demonstrated by a clear correlation observed between the CFD predictions and established experimental data, thereby affirming its capability for accurate simulation of aerodynamic phenomena. Results from both the numerical and experimental investigations consistently indicate that the asymmetric airfoil profile attains a superior lift‑to‑drag ratio compared to its symmetric counterpart.
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