Abstract
The self-noise of NACA 0012 and NACA 0021 airfoils are recorded at a Reynolds numbers of 96,000 in an anechoic wind tunnel at an angle-of-attack range of \(-5^\circ \)–\(40^\circ \). Results suggest that the low angle-of-attack tonal noise of the airfoils behaves differently, with the NACA 0021 producing tones at much higher angles-of-attack but not near \(0^\circ \). Noise generated at the onset of stall is subtlely different, with signature of the NACA 0012 forming over a larger angular range compared to the NACA 0021 where the stall signature forms suddenly.
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Laratro, A., Arjomandi, M., Cazzolato, B., Kelso, R. (2016). A Comparison of NACA 0012 and NACA 0021 Self-noise at Low Reynolds Number. In: Zhou, Y., Lucey, A., Liu, Y., Huang, L. (eds) Fluid-Structure-Sound Interactions and Control. Lecture Notes in Mechanical Engineering. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-662-48868-3_3
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DOI: https://doi.org/10.1007/978-3-662-48868-3_3
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