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An analytical model for predicting rotor broadband noise due to turbulent boundary layer ingestion.

An analytical model for predicting rotor broadband noise due to turbulent boundary layer ingestion.
An analytical model for predicting rotor broadband noise due to turbulent boundary layer ingestion.
Amiet’s model for the prediction of leading-edge noise produced by a rotor ingesting turbulence has been modified to account for the ingestion of a turbulent boundary layer. This model is compared to experimental data and is used to model the effect of changing the integral length scale of the turbulence on the noise spectrum. With blade-to-blade correlation modelled, the only effect of changing the integral length scale is to change the amplitude of the spectrum and significantly the shape of the spectrum is not changed. This work provides an insight into a method for choosing a suitable integral length scale without the need for experimental or computational fluid dynamics (CFD) data. This could potentially be useful for preliminary design studies where a fast approximation of the noise is required with minimal input data.
Karve, Ravish
e42d4414-7a27-451a-9ab4-5a0b33627469
Angland, David
b86880c6-31fa-452b-ada8-4bbd83cda47f
Gill, James
1e31eb24-f833-462e-b610-23b5b28e7285
Karve, Ravish
e42d4414-7a27-451a-9ab4-5a0b33627469
Angland, David
b86880c6-31fa-452b-ada8-4bbd83cda47f
Gill, James
1e31eb24-f833-462e-b610-23b5b28e7285

Karve, Ravish, Angland, David and Gill, James (2016) An analytical model for predicting rotor broadband noise due to turbulent boundary layer ingestion. Royal Aeronautical Society 2016 Applied Aerodynamics Conference, United Kingdom. 19 - 21 Jul 2016.

Record type: Conference or Workshop Item (Paper)

Abstract

Amiet’s model for the prediction of leading-edge noise produced by a rotor ingesting turbulence has been modified to account for the ingestion of a turbulent boundary layer. This model is compared to experimental data and is used to model the effect of changing the integral length scale of the turbulence on the noise spectrum. With blade-to-blade correlation modelled, the only effect of changing the integral length scale is to change the amplitude of the spectrum and significantly the shape of the spectrum is not changed. This work provides an insight into a method for choosing a suitable integral length scale without the need for experimental or computational fluid dynamics (CFD) data. This could potentially be useful for preliminary design studies where a fast approximation of the noise is required with minimal input data.

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e-pub ahead of print date: 19 July 2016
Venue - Dates: Royal Aeronautical Society 2016 Applied Aerodynamics Conference, United Kingdom, 2016-07-19 - 2016-07-21
Organisations: Aeronautics, Astronautics & Comp. Eng

Identifiers

Local EPrints ID: 405574
URI: https://eprints.soton.ac.uk/id/eprint/405574
PURE UUID: 04fa3d41-e07f-4ad2-8240-805e1e7595fe

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Date deposited: 08 Feb 2017 11:34
Last modified: 05 Oct 2018 12:04

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