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Aeroacoustics source mechanisms of fixed-wing VTOL configuration

Aeroacoustics source mechanisms of fixed-wing VTOL configuration
Aeroacoustics source mechanisms of fixed-wing VTOL configuration
This paper is a predominantly experimental investigation into the noise generation mechanisms of Fixed-wing Vertical Take-Off and Landing (VTOL) propeller – wing configurations. These new aircraft combine the benefits of being able to land vertically in urban areas while being able to fly like conventional propeller-driven aircraft. However, their unique arrangement of wing and propeller that can rotate relative to the wing leads to aeroacoustic source mechanisms that have never, or are poorly, understood. During forward flight the aeroacoustic mechanisms of propeller-wing interaction have been studied theoretically and experimentally in recent work. However, during transition, and particularly during vertical takeoff, the flow from the propeller is incident upon the wing at high incidence angle, leading to new source mechanisms and balance of sources. This paper reports the results of acoustic and velocity measurements of a scale-model propeller adjacent to a flat plate or wing for the purpose of identifying and characterising the dominant noise generation mechanisms of propeller -wing interaction. In this paper we focus on the hover condition and investigate the variation in noise due to the vertical separation distance and horizontal offset distance. The paper will demonstrate that the overall noise is the summation of the noise due to the interaction of the tip vortex of the propeller with the wing leading edge, rotor-alone noise, potential field interactions at close separation distance, turbulent-wing interaction at larger separation distance, and the interference effects due to reflections from the wing. The balance of these various sources with vertical and horizontal separation distance is explored.
2023-4293
Aerospace Research Central
Paruchuri, Chaitanya
5c1def64-6347-4be3-ac2d-b9f6a314b81d
Palleja-Cabre, Sergi
b841a96c-05d1-4f08-a197-8693cb3a3f90
Joseph, Phillip
9c30491e-8464-4c9a-8723-2abc62bdf75d
Akiwate, Deepak C.
b6f50d26-e59b-413e-9c66-0ee0a869813c
Westcott, Oliver
ab2090d6-fa00-44dc-b64d-5346c60a929b
Ferraro, Mario
bb685634-3a36-49dd-bd2e-ade3f475796c
Paruchuri, Chaitanya
5c1def64-6347-4be3-ac2d-b9f6a314b81d
Palleja-Cabre, Sergi
b841a96c-05d1-4f08-a197-8693cb3a3f90
Joseph, Phillip
9c30491e-8464-4c9a-8723-2abc62bdf75d
Akiwate, Deepak C.
b6f50d26-e59b-413e-9c66-0ee0a869813c
Westcott, Oliver
ab2090d6-fa00-44dc-b64d-5346c60a929b
Ferraro, Mario
bb685634-3a36-49dd-bd2e-ade3f475796c

Paruchuri, Chaitanya, Palleja-Cabre, Sergi, Joseph, Phillip, Akiwate, Deepak C., Westcott, Oliver and Ferraro, Mario (2023) Aeroacoustics source mechanisms of fixed-wing VTOL configuration. In AIAA AVIATION 2023 Forum Proceedings. Aerospace Research Central.. (doi:10.2514/6.2023-3356).

Record type: Conference or Workshop Item (Paper)

Abstract

This paper is a predominantly experimental investigation into the noise generation mechanisms of Fixed-wing Vertical Take-Off and Landing (VTOL) propeller – wing configurations. These new aircraft combine the benefits of being able to land vertically in urban areas while being able to fly like conventional propeller-driven aircraft. However, their unique arrangement of wing and propeller that can rotate relative to the wing leads to aeroacoustic source mechanisms that have never, or are poorly, understood. During forward flight the aeroacoustic mechanisms of propeller-wing interaction have been studied theoretically and experimentally in recent work. However, during transition, and particularly during vertical takeoff, the flow from the propeller is incident upon the wing at high incidence angle, leading to new source mechanisms and balance of sources. This paper reports the results of acoustic and velocity measurements of a scale-model propeller adjacent to a flat plate or wing for the purpose of identifying and characterising the dominant noise generation mechanisms of propeller -wing interaction. In this paper we focus on the hover condition and investigate the variation in noise due to the vertical separation distance and horizontal offset distance. The paper will demonstrate that the overall noise is the summation of the noise due to the interaction of the tip vortex of the propeller with the wing leading edge, rotor-alone noise, potential field interactions at close separation distance, turbulent-wing interaction at larger separation distance, and the interference effects due to reflections from the wing. The balance of these various sources with vertical and horizontal separation distance is explored.

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More information

e-pub ahead of print date: 8 June 2023
Venue - Dates: AIAA AVIATION 2023 Forum, , San Diego, United States, 2023-06-12 - 2023-06-16

Identifiers

Local EPrints ID: 478705
URI: http://eprints.soton.ac.uk/id/eprint/478705
ISSN: 2023-4293
PURE UUID: 497f71e2-4d83-42b9-86dd-0fd6df698900
ORCID for Sergi Palleja-Cabre: ORCID iD orcid.org/0000-0002-5414-7716
ORCID for Deepak C. Akiwate: ORCID iD orcid.org/0000-0002-9135-7886

Catalogue record

Date deposited: 07 Jul 2023 16:41
Last modified: 17 Mar 2024 03:48

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Contributors

Author: Phillip Joseph
Author: Deepak C. Akiwate ORCID iD
Author: Oliver Westcott
Author: Mario Ferraro

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