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NUMERICAL INVESTIGATIONS ON SMALL-SCALE ROTOR CONFIGURATIONS WITH VALIDATION USING ACOUSTIC WIND TUNNEL DATA

Yin, Jianping and Rossignol, Karl-Stephane and Rottmann, Lukas and Schwarz, Thorsten (2022) NUMERICAL INVESTIGATIONS ON SMALL-SCALE ROTOR CONFIGURATIONS WITH VALIDATION USING ACOUSTIC WIND TUNNEL DATA. In: 48th European Rotorcraft Forum, ERF 2022, pp. 1-17. 48th European Rotorcraft Forum (ERF) 2022, 6.- 8. September 2022, Winterthur, Switzerland. ISBN 978-171387029-6.

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Official URL: https://www.zhaw.ch/de/engineering/institute-zentren/zav/veranstaltungen/erf2022/

Abstract

This paper addresses the acoustic and aerodynamic characteristics of small-scale rotor configurations, including the influence of the rotor-rotor interactions. For this purpose, a Rotor/Rotor/Pylon configuration is chosen for both the test and numerical simulations. The wind tunnel experiments on various rotor configuration were performed in DLR’s Acoustic Wind Tunnel Braunschweig (AWB). The experiments involve isolated rotors, and rotors in tandem and coaxial configuration in hover and forward flight. For numerical simulations an unsteady free wake 3-D panel method (UPM) is used to account for aerodynamic non-linear effects associated with the mutual interference among the Rotor/Rotor/Pylon configurations. The effect of the pylon is simulated using potential theory in form of a panelized body. Finally, the sound propagation into the far field is calculated with DLR’s FW-H code APSIM, using UPM blade surface pressure as input. The validation effort is supported by CFD TAU steady simulations on selected hover test cases. The experiments and numerical results indicate that the harmonic noise is the dominant source of the noise for the present rotor selection. Broadband noise is also observed in the experiment, but its contribution to the overall sound pressure is small. In the numerical simulations of both the coaxial and the tandem configuration, the interferences are particularly well visible and the noise directivity becomes more complex. There is no change in time averaged inflow by applying phase angles. In the coaxial condition, in hover, the phase delay between rotors doesn’t change the maximum noise level. In forward flight, the phase delay can influence the maximum level of the noise radiation. In both coaxial and tandem configuration, the position of the downstream rotor is key for the noise radiation and therefore avoiding the interaction with upstream wake can reduce the noise radiation.

Item URL in elib:https://elib.dlr.de/190347/
Document Type:Conference or Workshop Item (Speech)
Title:NUMERICAL INVESTIGATIONS ON SMALL-SCALE ROTOR CONFIGURATIONS WITH VALIDATION USING ACOUSTIC WIND TUNNEL DATA
Authors:
AuthorsInstitution or Email of AuthorsAuthor's ORCID iDORCID Put Code
Yin, JianpingUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Rossignol, Karl-StephaneUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Rottmann, LukasUNSPECIFIEDUNSPECIFIEDUNSPECIFIED
Schwarz, ThorstenUNSPECIFIEDhttps://orcid.org/0000-0003-1034-6120UNSPECIFIED
Date:September 2022
Journal or Publication Title:48th European Rotorcraft Forum, ERF 2022
Refereed publication:Yes
Open Access:No
Gold Open Access:No
In SCOPUS:Yes
In ISI Web of Science:No
Page Range:pp. 1-17
Editors:
EditorsEmailEditor's ORCID iDORCID Put Code
UNSPECIFIEDZHAWUNSPECIFIEDUNSPECIFIED
ISBN:978-171387029-6
Status:Published
Keywords:Helicopter Acoustics, Acoustic Wind Tunnel, Urban Air Mobility (UAM), Unsteady Panel Method, acoustic analogy, CFD,SMALL-SCALE ROTOR CONFIGURATIONS
Event Title:48th European Rotorcraft Forum (ERF) 2022
Event Location:Winterthur, Switzerland
Event Type:international Conference
Event Dates:6.- 8. September 2022
Organizer:the Centre for Aviation (ZAV) of the ZHAW Zurich University of Applied Sciences
HGF - Research field:Aeronautics, Space and Transport
HGF - Program:Aeronautics
HGF - Program Themes:Efficient Vehicle
DLR - Research area:Aeronautics
DLR - Program:L EV - Efficient Vehicle
DLR - Research theme (Project):L - Virtual Rotorcraft and Validation
Location: Braunschweig
Institutes and Institutions:Institute for Aerodynamics and Flow Technology > Helicopter, BS
Institute for Aerodynamics and Flow Technology > Technical Acoustics
Deposited By: Yin, Dr.-Ing. Jianping
Deposited On:25 Nov 2022 12:14
Last Modified:04 Sep 2023 09:11

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