Numerical Simulation of Wavy-Flap Airfoil Performance at Low Reynolds Number: Insights from Lift and Drag Coefficient Analysis

Abstract

This research examines the aerodynamic performance of wavy (corrugated) airfoils, focusing specifically on analyzing the impact of two angles of attack: the airfoil's angle of attack and the tail's angle of attack (beta). Simulations were conducted using the W1011 airfoil at a Reynolds number of 200,000, considering attack angles of 0, 2, 5, and 8 degrees for the airfoil, and 0, 10, 20, 30, and 40 degrees for the tail. The simulation outcomes were validated against experimental data from Williamson's laboratory. The findings indicate a notable increase in the lift coefficient for the wavy airfoils, especially at larger flap angles. Specifically, at a beta of 40 degrees, the lift coefficient of the wavy airfoil at a 10-degree angle of attack was nearly three times greater than in the other scenarios. In contrast, the drag coefficient also increased, but to a lesser extent, which suggests enhanced aerodynamic efficiency. Furthermore, the lift to drag ratio was significantly higher for the wavy airfoils, particularly at lower angles of attack. Overall, the study concludes that wavy airfoils, especially with higher tail angles, offer considerable aerodynamic benefits, especially in conditions of low angle attack, improving lift and fuel efficiency for use in both aviation and marine applications.