Investigation of Aerodynamics Performance Towards Effect Separation Location on NACA 4415 Airfoil with Computational Method

James Julian; Waridho Iskandar; Fitri Wahyuni; Muhammad Ilham Adhynugraha; Fadilah Hasim; Mohammand Amanta Kumala Sakti; Fadli Cahya Megawanto

doi:10.15866/irea.v11i4.22131

Investigation of Aerodynamics Performance Towards Effect Separation Location on NACA 4415 Airfoil with Computational Method

James Julian^(1*), Waridho Iskandar⁽²⁾, Fitri Wahyuni⁽³⁾, Muhammad Ilham Adhynugraha⁽⁴⁾, Fadilah Hasim⁽⁵⁾, Mohammand Amanta Kumala Sakti⁽⁶⁾, Fadli Cahya Megawanto⁽⁷⁾

^(*) Corresponding author

Authors' affiliations

DOI: https://doi.org/10.15866/irea.v11i4.22131

Abstract

NACA 4415 is an airfoil commonly used in wind turbines and aircraft wing. This study uses computational method with type C grid with variations in grid elements 5×102, 5×103, and 5×104. From the grid independence test, grid with 5×104 elements are the most suitable to get the best computational results. The turbulence model in this study is standard k-ε. From the computational results, the best Cl is found at the interval -9°≤ α ≤15°. In comparison, the best Cd is in the interval -7°≤ α ≤15°. Meanwhile, for Cm, the best data is obtained at the interval -7°≤ α ≤10°, where the Cm gradient increases or decreases not too extreme. However, from Cl/Cd analysis, the best performance of NACA 4415 is at -7°≤ α ≤6°. Outside of that interval, the performance tends to decrease due to the influence of separation. Those are evident from separation point starting at α=11° where the position is in x/c=0.165, and as α increases, the position of the separation point will get closer to the leading edge. On the lower side of the airfoil, the separation begins to form at α=-11° and will get closer to the leading edge when the airfoil reduces α as in α=-15°.
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Keywords

Aerodynamic; Airfoil; Performance; Separation; Turbulence

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