Experimental results for supersonic jet noise reduction using nozzle fluidic inserts

Jessica Morgan, Dennis K. McLaughlin, Philip J. Morris

Research output: Chapter in Book/Report/Conference proceedingConference contribution

12 Scopus citations


This paper describes further development of an active noise reduction method using fluidic inserts. Fluidic inserts blow bypassed air into the divergent section of a convergingdiverging nozzle and are actively controlled to minimize effects on engine performance. The fluidic inserts are aligned in the nozzle to create a corrugation simulating the effect of a hard-wall corrugations. Previous studies have shown that the fluidic insert method reduces both the peak mixing noise and the broadband shock associated noise. The goal of the current research is the optimization of the fluidic insert noise reduction method through parametric studies. The present study focuses on varying the number of fluidic corrugations and their azimuthal positions. Noise measurements using four fluidic corrugations with both evenly spaced and unevenly spaced azimuthal positions are compared to previous experiments with three and six evenly space fluidic corrugations.

Original languageEnglish (US)
Title of host publication23rd AIAA/CEAS Aeroacoustics Conference, 2017
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105043
StatePublished - Jan 1 2017
Event23rd AIAA/CEAS Aeroacoustics Conference, 2017 - Denver, United States
Duration: Jun 5 2017Jun 9 2017

Publication series

Name23rd AIAA/CEAS Aeroacoustics Conference, 2017


Other23rd AIAA/CEAS Aeroacoustics Conference, 2017
Country/TerritoryUnited States

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Electrical and Electronic Engineering


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