Numerical Simulations of High-lift Configurations on a NACA4412 Airfoil
DOI:
https://doi.org/10.5433/1679-0375.2025.v46.53227Keywords:
NACA 4412, high-lift devices, aerodynamics performance, CFD, flapAbstract
This study examines the performance of different high-lift device configurations applied to a NACA 4412 airfoil, highlighting their respective advantages and disadvantages. Numerical simulations were performed using the open-source CFD code OpenFOAM® for five distinct configurations—plain flap, split flap, slotted flap, Fowler flap, and Junkers flap—under equivalent conditions, enabling a consistent comparison of results. All flaps were deflected by 10° and analyzed at a Reynolds number of 1.7 × 10⁵ over an angle-of-attack range from −4° to 16°. The Spalart–Allmaras turbulence model was adopted in all steady-state simulations. Quantitative analyses were conducted for the lift (Cl) and drag (Cd) coefficients per unit length, as well as for the pressure coefficient (Cp) on the airfoil surfaces, in addition to the velocity and pressure flow fields. The results demonstrated reliable and consistent predictions of lift and drag generation; however, convergence difficulties were observed at angles of attack near stall conditions. Furthermore, the simulations revealed superior lift performance for flap configurations commonly employed in the aeronautical industry, particularly the slotted flap and the Fowler flap.
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