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Publication
Mitigating Dynamic Stall with a Movable Leading-Edge: the NACA0012-IK30 Wing
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Advisor(s)
Abstract(s)
One major problem that affects rotor blade aerodynamics is dynamic stall, characterized by a series of events where transient vortex shedding negatively affects drag and lift, leading to abrupt changes in the wing’s pitching moment. The present work focuses on the mitigation of such effects by using a modified NACA0012 airfoil: the NACA0012-IK30 airfoil, used previously for thrust enhancement in flapping propulsion. An experimental rig is designed and built to study the advantages of a time-varying pitching leading edge on a plunging wing, more specifically its influence on the aerodynamic coefficients over time. Results indicate that when the wing is not experiencing significant stall, the movable leading edge does not hold considerable influence on drag or lift. However, it can reduce the pitching moment intensity by indirectly shifting the pressure center. Contrarily, when the wing is under proper dynamic stall, the movable leading edge truly improves the aerodynamic characteristics while operating at smaller effective angles of attack. This study contributes to the long-standing discussion on how to mitigate the adverse effects of dynamic stall by providing an innovative yet simple solution.
Description
Keywords
Dynamic stall Force measurements Movable leading-edge Flow control
Pedagogical Context
Citation
Camacho, E.A.R., Silva, A.R.R., Marques, F.D. Mitigating Dynamic Stall with a Movable Leading-Edge: the NACA0012-IK30 Wing 34th Congress of the International Council of the Aeronautical Sciences, ICAS 2024, Florença, Itália, 9-13 setembro 2024
Publisher
International Council of the Aeronautical Sciences