Numerical predictions of Low-Reynolds-Number propeller aeroacoustics: comparison of methods at different fidelity levels

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dc.contributor.authorHuang, Guangyuan
dc.contributor.authorSharma, Ankit
dc.contributor.authorChen, Xin
dc.contributor.authorRiaz, Atif
dc.contributor.authorJefferson-Loveday, Richard
dc.date.accessioned2025-03-26T10:58:05Z
dc.date.available2025-03-26T10:58:05Z
dc.date.freetoread2025-03-26
dc.date.issued2025-02-18
dc.date.pubOnline2025-02-18
dc.descriptionThis article belongs to the Special Issue New Developments in Aeroacoustics Research: From Fundamentals to Applications
dc.description.abstractLow-Reynolds-number propeller systems have been widely used in aeronautical applications, such as unmanned aerial vehicles (UAV) and electric propulsion systems. However, the aerodynamic sound of the propeller systems is often significant and can lead to aircraft noise problems. Therefore, effective predictions of propeller noise are important for designing aircraft, and the different phases in aircraft design require specific prediction approaches. This paper aimed to perform a comparison study on numerical methods at different fidelity levels for predicting the aerodynamic noise of low-Reynolds-number propellers. The Ffowcs-Williams and Hawkings (FWH), Hanson, and Gutin methods were assessed as, respectively, high-, medium-, and low-fidelity noise models. And a coarse-grid large eddy simulation was performed to model the propeller aerodynamics and to inform the three noise models. A popular propeller configuration, which has been used in previous experimental and numerical studies on propeller noise, was employed. This configuration consisted of a two-bladed propeller mounted on a cylindrical nacelle. The propeller had a diameter of D=9″ and a pitch-to-diameter ratio of P/D=1, and was operated in a forward-flight condition with a chord-based Reynolds number of Re=4.8×104, a tip Mach number of M=0.231, and an advance ratio of J=0.485. The results were validated against existing experimental measurements. The propeller flow was characterized by significant tip vortices, weak separation over the leading edges of the blade suction sides, and small-scale vortical structures from the blade trailing edges. The far-field noise was characterized by tonal noise, as well as broadband noise. The mechanism of the noise generation and propagation were clarified. The capacities of the three noise modeling methods for predicting such propeller noise were evaluated and compared.
dc.description.journalNameAerospace
dc.description.sponsorshipThis research was funded by Innovate UK, Aerospace Technology Institute (ATI), UK grant number 10003388
dc.identifier.citationHuang G, Sharma A, Chen X, et al., (2025) Numerical predictions of Low-Reynolds-Number propeller aeroacoustics: comparison of methods at different fidelity levels. Aerospace, Volume 12, Issue 2, February 2025, Article number 154
dc.identifier.eissn2226-4310
dc.identifier.elementsID564865
dc.identifier.issn2226-4310
dc.identifier.issueNo2
dc.identifier.paperNo154
dc.identifier.urihttps://doi.org/10.3390/aerospace12020154
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/23648
dc.identifier.volumeNo12
dc.languageEnglish
dc.language.isoen
dc.publisherMDPI
dc.publisher.urihttps://www.mdpi.com/2226-4310/12/2/154
dc.rightsAttribution 4.0 Internationalen
dc.rights.urihttp://creativecommons.org/licenses/by/4.0/
dc.subjectcomputational aeroacoustics
dc.subjectlow-Reynolds-number propeller
dc.subjectmulti-fidelity modeling
dc.subjectaircraft design
dc.subject4012 Fluid Mechanics and Thermal Engineering
dc.subject4007 Control Engineering, Mechatronics and Robotics
dc.subject40 Engineering
dc.subject4001 Aerospace Engineering
dc.subject7 Affordable and Clean Energy
dc.subject4001 Aerospace engineering
dc.titleNumerical predictions of Low-Reynolds-Number propeller aeroacoustics: comparison of methods at different fidelity levels
dc.typeArticle
dc.type.subtypeJournal Article
dcterms.dateAccepted2025-02-07

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