Impact of tip-vortex modeling uncertainty on helicopter rotor blade-vortex interaction noise prediction

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dc.contributor.authorVouros, Stavros
dc.contributor.authorGoulos, Ioannis
dc.contributor.authorScullion, Calum
dc.contributor.authorNalianda, Devaiah
dc.contributor.authorPachidis, Vassilios
dc.date.accessioned2020-09-17T15:51:00Z
dc.date.available2020-09-17T15:51:00Z
dc.date.issued2020-09-04
dc.description.abstractFree-wake models are routinely used in aeroacoustic analysis of helicopter rotors; however, their semi-empiricism is accompanied with uncertainty related to the modeling of physical wake parameters. In some cases, analysts have to resort to empirical adaption of these parameters based on previous experimental evidence. This paper investigates the impact of inherent uncertainty in wake aerodynamic modeling on the robustness of helicopter rotor aeroacoustic analysis. A free-wake aeroelastic rotor model is employed to predict high-resolution unsteady airloads, including blade-vortex interactions. A rotor aeroacoustics model, based on integral solutions of the Ffowcs Williams-Hawkings equation, is utilized to calculate aerodynamic noise in the time-domain. The individual analytical models are incorporated into an uncertainty analysis numerical procedure, implemented through non-intrusive Polynomial Chaos expansion. The potential sources of uncertainty in wake tip-vortex core growth modeling are identified and their impact on noise predictions is systematically quantified. When experimental data to adjust the tip-vortex core model are not available the uncertainty in acoustic pressure and noise impact at observers dominated by blade-vortex interaction noise can reach up to 25% and 3.50 dB respectively. A set of generalized uncertainty maps is derived, for use as modeling guidelines for aeroacoustic analysis in the absence of the robust evidence necessary for calibration of semi-empirical vortex core models.en_UK
dc.identifier.citationVouros S, Goulos I, Scullion C, Nalianda D, et al., (2020) mpact of tip-vortex modeling uncertainty on helicopter rotor blade-vortex interaction noise prediction. Journal of the American Helicopter Society, Volume 66, number 1, January 2021, pp. 1-13en_UK
dc.identifier.issn0002-8711
dc.identifier.urihttps://doi.org/10.4050/JAHS.66.012005
dc.identifier.urihttps://dspace.lib.cranfield.ac.uk/handle/1826/15813
dc.language.isoenen_UK
dc.publisherVertical Flight Societyen_UK
dc.rightsAttribution-NonCommercial 4.0 International*
dc.rights.urihttp://creativecommons.org/licenses/by-nc/4.0/*
dc.subjectBlade-vortex interaction noiseen_UK
dc.subjectUncertainty quantificationen_UK
dc.subjectHelicopter noise predictionen_UK
dc.subjectFree-wake aerodynamicsen_UK
dc.titleImpact of tip-vortex modeling uncertainty on helicopter rotor blade-vortex interaction noise predictionen_UK
dc.typeArticleen_UK

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