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Keywords
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aerodynamics, fluid dynamics, wavy-flap-airfoil, numerical simulation, low-Reynolds
number, lift coefficient, drag coefficient
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Abstract
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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 0◦, 2◦, 5◦, and 8◦, and tail angles of 0◦, 10◦, 20◦, 30◦, and 40◦. Results were
validated against experimental data from Williamson’s lab. Findings show a notable
lift coefficient increase, especially at higher flap angles. At 𝛽 = 40◦ and 0◦ 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.
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