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Aerodynamic and Aeroacoustic Optimization of Leading-Edge Undulation of a NACA 65(12)-10 Airfoil

Kim, J-H., Choi, K-S., Lacagnina, G. , Chaitanya, P., Joseph, P., Hasheminejad, S. M., Chong, T. P., Shahab, M. F., Omidyeganeh, M. ORCID: 0000-0002-4140-2810 & Pinelli, A. (2022). Aerodynamic and Aeroacoustic Optimization of Leading-Edge Undulation of a NACA 65(12)-10 Airfoil. AIAA JOURNAL, 60(4), pp. 2342-2353. doi: 10.2514/1.j060716


Experimental studies of a NACA 65(12)-10 airfoil with a sinusoidal leading-edge undulation (LEU) were carried out to simultaneously optimize its aerodynamic and aeroacoustic performances by considering the attached as well as the separated flow at the effective Reynolds number of 106, where the maximum lift was increased without sacrificing drag or overall noise at near- and poststall angles. Further aerodynamic and aeroacoustic tests indicated that a combination of LEU wavelength λ/c=30% and amplitude h/c=6% gave an optimum LEU by considering the aerodynamic performance as well as the noise reduction. Particle image velocimetry measurements of the flow over the optimized airfoil showed biperiodic velocity fluctuations downstream of the LEU peaks that were associated with unsteady stall cell structure near the trailing edge.

Publication Type: Article
Additional Information: Copyright © 2021 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. All requests for copying and permission to reprint should be submitted to CCC at; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions
Publisher Keywords: Trailing Edges, Symmetric Airfoil, Aerodynamic Performance, Aerodynamic Characteristics, Particle Image Velocimetry, Separated Flows, Boundary Layer Transition, Mean Camber Line, Freestream Turbulence, Aspect Ratio
Subjects: T Technology > TJ Mechanical engineering and machinery
T Technology > TL Motor vehicles. Aeronautics. Astronautics
Departments: School of Science & Technology > Engineering
SWORD Depositor:
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