TY - GEN
T1 - Analysis of fluid insert noise reduction method with PIV
AU - Morgan, Jessica
AU - Shoemaker, Christopher
AU - McLaughlin, Dennis K.
AU - Morris, Philip J.
AU - Berger, Zachary P.
N1 - Funding Information:
This work was performed under the sponsorship of the Office of Naval Research with Contract N00014-14-C-0157 and Dr. K. Millsaps serving as Project Monitor and Dr. Steven Martens is a Co-Principal Investigator. The views and conclusions contained herein are those of the authors and do not represent the opinion of the Office of Naval Research or the U.S. government.
Publisher Copyright:
© 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2018
Y1 - 2018
N2 - The fluid flow field of a supersonic jet from a converging-diverging nozzle with fluid inserts is studied in an experimental investigation. The Pennsylvania State University has developed a noise reduction method that uses corrugations or rows of fluid inserts in the diverging section of the nozzle. Far-field pressure measurements have successfully shown up to a 5 dB noise reduction in the peak noise direction. The current study utilizes Particle Image Velocimetry (PIV) to observe the near-field velocities directly at the exit plane of the nozzle. The flow field is analyzed and compared for various fluid insert configurations. The velocity field demonstrates the effect of the fluid inserts on the core flow of the jet. It is observed that the fluid inserts increase the width of the shear layer. A filtered Proper orthogonal decomposition (POD) method is discussed in the analysis of the flow field. The flow field results are compared to far-field measurements to better understand the mechanisms that produce noise reduction.
AB - The fluid flow field of a supersonic jet from a converging-diverging nozzle with fluid inserts is studied in an experimental investigation. The Pennsylvania State University has developed a noise reduction method that uses corrugations or rows of fluid inserts in the diverging section of the nozzle. Far-field pressure measurements have successfully shown up to a 5 dB noise reduction in the peak noise direction. The current study utilizes Particle Image Velocimetry (PIV) to observe the near-field velocities directly at the exit plane of the nozzle. The flow field is analyzed and compared for various fluid insert configurations. The velocity field demonstrates the effect of the fluid inserts on the core flow of the jet. It is observed that the fluid inserts increase the width of the shear layer. A filtered Proper orthogonal decomposition (POD) method is discussed in the analysis of the flow field. The flow field results are compared to far-field measurements to better understand the mechanisms that produce noise reduction.
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U2 - 10.2514/6.2018-3610
DO - 10.2514/6.2018-3610
M3 - Conference contribution
AN - SCOPUS:85051300460
SN - 9781624105609
T3 - 2018 AIAA/CEAS Aeroacoustics Conference
BT - 2018 AIAA/CEAS Aeroacoustics Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA/CEAS Aeroacoustics Conference, 2018
Y2 - 25 June 2018 through 29 June 2018
ER -