Numerical Investigation of a Trailing-Edge Extension on the NACA ۶۳-۴۱۵ Airfoil

The aerodynamic effects of a simplified trailing-edge extension inspired by serrated trailing edges are investigated for the NACA ۶۳-۴۱۵ airfoil using two-dimensional Reynolds-averaged Navier–Stokes simulations. The numerical approach is validated against existing experimental and numerical data, showing good agreement for the baseline airfoil. Simulations are conducted for Reynolds numbers between ۵×۱۰۵ and ۳×۱۰۶ and angles of attack from ۰ to ۲۰∘. The trailing-edge extension is found to significantly increase lift across all Reynolds numbers, with maximum lift enhancements of approximately ۲۳–۲۸% near stall. Aerodynamic efficiency improves at low angles of attack but decreases at higher angles due to increased drag. Pressure and flow-field analyses indicate that lift enhancement results from sustained pressure loading over an extended chordwise length, while the drag increase is associated with an elongated near-wake recirculation region.

کلیدواژه ها:

Wind turbine airfoils ، Trailing-edge modification ، Passive flow control