TY - JOUR
T1 - Reducing the noise emanating from a twin jet nozzle using flexible filaments Topics in Flow Control. Guest editors J.P. Bonnet and L. Cattafesta
AU - Lucas, Nathaniel
AU - Doty, Michael
AU - Taubert, Lutz
AU - Wygnanski, Israel
N1 - Funding Information:
We would like to acknowledge the assistance of Dr. Jesse Little, who was very helpful in making sure the results and background information were framed in the proper context with respect to other aeroacoustics research that has been done in the past, and Philipp Tewes, who contributed to the data processing effort. Many thanks to Harry Haskin, John Swartzbaugh, and the rest of the NASA JNL crew for the exciting opportunity to collaborate our research. Funding for the NASA tests from the NASA Langley Research Directorate Office and the Fundamental Aeronautics Program Supersonics Project is gratefully acknowledged.
PY - 2013/4
Y1 - 2013/4
N2 - A twin jet was tested in anechoic facilities at the University of Arizona and NASA Langley Research Center to determine the effectiveness of flexible filaments in jet noise reduction. Results were strongly dependent on filament diameter and material, the most effective of which was found to be Tex 800 Kevlar. In the best configurations, the filaments consistently eliminated screech tones and reduced overall sound pressure level by 3 dB or more. Additionally, broadband shock noise was diminished by more than 5 dB over certain audible frequency ranges. Larger-scale tests run at NASA showed comparable reductions in overall sound pressure level and broadband shock-associated noise.
AB - A twin jet was tested in anechoic facilities at the University of Arizona and NASA Langley Research Center to determine the effectiveness of flexible filaments in jet noise reduction. Results were strongly dependent on filament diameter and material, the most effective of which was found to be Tex 800 Kevlar. In the best configurations, the filaments consistently eliminated screech tones and reduced overall sound pressure level by 3 dB or more. Additionally, broadband shock noise was diminished by more than 5 dB over certain audible frequency ranges. Larger-scale tests run at NASA showed comparable reductions in overall sound pressure level and broadband shock-associated noise.
UR - http://www.scopus.com/inward/record.url?scp=84877824345&partnerID=8YFLogxK
U2 - 10.1007/s00348-013-1504-8
DO - 10.1007/s00348-013-1504-8
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AN - SCOPUS:84877824345
SN - 0723-4864
VL - 54
JO - Experiments in Fluids
JF - Experiments in Fluids
IS - 4
M1 - 1504
ER -