Please use this identifier to cite or link to this item:
http://hdl.handle.net/10397/106466
DC Field | Value | Language |
---|---|---|
dc.contributor | Department of Mechanical Engineering | - |
dc.creator | Lam, GCY | - |
dc.creator | Leung, RCK | - |
dc.date.accessioned | 2024-05-09T00:53:43Z | - |
dc.date.available | 2024-05-09T00:53:43Z | - |
dc.identifier.issn | 0001-1452 | - |
dc.identifier.uri | http://hdl.handle.net/10397/106466 | - |
dc.language.iso | en | en_US |
dc.publisher | American Institute of Aeronautics and Astronautics, Inc. | en_US |
dc.rights | Copyright © 2018 by Garret C. Y. Lam and Randolph C. K. Leung. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. | en_US |
dc.rights | This is the peer reviewed version of the following article: Lam, G. C. Y., & Leung, R. C. K. (2018). Aeroacoustics of NACA 0018 Airfoil with a Cavity. AIAA Journal, 56(12), 4775-4786, which has been published in final form at https://doi.org/10.2514/1.J056389. | en_US |
dc.title | Aeroacoustics of NACA 0018 airfoil with a cavity | en_US |
dc.type | Journal/Magazine Article | en_US |
dc.identifier.spage | 4775 | - |
dc.identifier.epage | 4786 | - |
dc.identifier.volume | 56 | - |
dc.identifier.issue | 12 | - |
dc.identifier.doi | 10.2514/1.J056389 | - |
dcterms.abstract | This paper reports a detailed numerical study of the aeroacoustics of a NACA 0018 airfoil with acavity at zero angle of attack, with chord-based Reynolds and freestream Mach numbers at 2 × 10⁴ and 0.2, in two dimensions. For an airfoil without a cavity, vortex shedding from the trailing edge and low-frequency wake flapping are found to be the major aeroacoustic processes. The presence of a cavity introduces additional acoustic generation due to cavity oscillation modes but weakens the noise sourceatthe airfoil trailing edge viaajittering of the flow. Three aeroacoustic mechanisms are identified with extensive fast Fourier transform, wavelet, and coherence analyses. The airfoil with cavity effectively increases the lift-to-drag ratio from almost zero (ordinary airfoil) to approximately 5.3. However, it radiates less acoustic power by 1.2 and by 2.6 dB from the airfoil upper and lower surfaces, respectively, even if the acoustic contribution of wake flapping of the ordinary airfoil is excluded. The outcomes of the study suggest that an airfoil with a cavity is a feasible configuration that gives high lift-to-drag ratio yet low noise generation, making it a promising quiet airfoil design at low Reynolds number. | - |
dcterms.accessRights | open access | en_US |
dcterms.bibliographicCitation | AIAA journal, Dec. 2018, v. 56, no. 12, p. 4775-4786 | - |
dcterms.isPartOf | AIAA journal | - |
dcterms.issued | 2018-12 | - |
dc.identifier.scopus | 2-s2.0-85051299084 | - |
dc.identifier.eissn | 1533-385X | - |
dc.description.validate | 202405 bcch | - |
dc.description.oa | Accepted Manuscript | en_US |
dc.identifier.FolderNumber | ME-0560 | en_US |
dc.description.fundingSource | Others | en_US |
dc.description.fundingText | Philip K. H. Wong Foundation; The Hong Kong Polytechnic University; State Key Laboratory of Mechanical System and Vibration of Shanghai Jiao Tong University | en_US |
dc.description.pubStatus | Published | en_US |
dc.identifier.OPUS | 21779134 | en_US |
dc.description.oaCategory | Green (AAM) | en_US |
Appears in Collections: | Journal/Magazine Article |
Files in This Item:
File | Description | Size | Format | |
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Lam_Aeroacoustics_Naca_Airfoil.pdf | Pre-Published version | 19.3 MB | Adobe PDF | View/Open |
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