TY - GEN
T1 - Effects of a noise reduction strategy applied to a supersonic jet impinging on an inclined flat plate
AU - Yenigelen, Evren
AU - Morris, Philip J.
N1 - Funding Information:
This work is a part of the Ph.D. research of the first author. The first two years of this Ph.D. program were funded by The Scientific and Technological Research Council of Turkey as a part of The BIDEB 2213 - Graduate Study Abroad Funding Program.
Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2021
Y1 - 2021
N2 - An acoustic investigation is one of the most important tasks during the design of a rocket launch vehicle, since near-field acoustic loads can be detrimental to the launch vehicle itself and far-field acoustic levels have a high impact on noise pollution around the launch site. In this study, the effect of a noise reduction method applied to a supersonic jet impinging on an inclined flat plate is investigated. Similar noise sources that are present in free-jet flows are also observed in impinging jets. However, the introduction of an impingement plate creates new acoustic sources. These sources are created by the impingement of the jet flow and the interaction of the acoustic waves that are created in the free-jet region with the impinging flow. The goal of this study is to gain insight into the acoustic sources that are present in a jet impinging on an inclined flat plate, while trying to attenuate the near-field and far-field noise levels by introducing a wall with a cut-out between the nozzle exit and the impingement plate. The aim of this strategy is to block the waves traveling upstream towards the launch vehicle as much as possible, containing the waves between the impingement plate and the wall with a cut-out. The effects of the location of the wall and the size of the cut-out are investigated by analyzing different setups, while trying not to disturb the flow significantly, as this would create new noise sources. The flow field is calculated by a Detached Eddy Simulation code and a computational aeroacoustics code, based on the Ffowcs Williams and Hawkings method, is used to extend the flow field results to the near and far-fields.
AB - An acoustic investigation is one of the most important tasks during the design of a rocket launch vehicle, since near-field acoustic loads can be detrimental to the launch vehicle itself and far-field acoustic levels have a high impact on noise pollution around the launch site. In this study, the effect of a noise reduction method applied to a supersonic jet impinging on an inclined flat plate is investigated. Similar noise sources that are present in free-jet flows are also observed in impinging jets. However, the introduction of an impingement plate creates new acoustic sources. These sources are created by the impingement of the jet flow and the interaction of the acoustic waves that are created in the free-jet region with the impinging flow. The goal of this study is to gain insight into the acoustic sources that are present in a jet impinging on an inclined flat plate, while trying to attenuate the near-field and far-field noise levels by introducing a wall with a cut-out between the nozzle exit and the impingement plate. The aim of this strategy is to block the waves traveling upstream towards the launch vehicle as much as possible, containing the waves between the impingement plate and the wall with a cut-out. The effects of the location of the wall and the size of the cut-out are investigated by analyzing different setups, while trying not to disturb the flow significantly, as this would create new noise sources. The flow field is calculated by a Detached Eddy Simulation code and a computational aeroacoustics code, based on the Ffowcs Williams and Hawkings method, is used to extend the flow field results to the near and far-fields.
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M3 - Conference contribution
AN - SCOPUS:85100252901
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 19
BT - AIAA Scitech 2021 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
Y2 - 11 January 2021 through 15 January 2021
ER -