Numerical simulation of wavy-flap airfoil performance at low Reynolds number: insights from lift and drag coefficient analysis

This research examines the aerodynamic performance of wavy (corrugated) airfoils, focusing on the effects of two angles of attack: the airfoil’s and the tail’s (β). Simulations used the W1011 airfoil at a Reynolds number of 200 000, with airfoil angles of 0o, 2o, 5o, and 8o, and tail angles of 0o, 10o, 20o, 30o, and 40o. Results were validated against experimental data from Williamson’s lab. Findings show a notable lift coefficient increase, especially at higher flap angles. At β = 40o and 0o airfoil angle, lift was nearly three times greater than other cases. While drag also increased, it was less significant, indicating better aerodynamic efficiency. The lift-to-drag ratio improved notably at lower attack angles but declined slightly at higher angles due to turbulence and low-pressure zones. Overall, wavy airfoils with larger tail angles provide aerodynamic advantages, especially at low angles of attack, enhancing lift and fuel efficiency in aviation and marine contexts.