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Decomposition of High Speed Jet Noise: Source Characteristics and Propagation Effects

Schlinker, R. H. and Simonich, J. C. and Reba, R. A. and Colonius, T. and Ladeinde, F. (2008) Decomposition of High Speed Jet Noise: Source Characteristics and Propagation Effects. In: 14th AIAA/CEAS Aeroacoustics Conference (29th AIAA Aeroacoustics Conference), 5-7 May 2008, Vancouver, Canada.

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Current research programs directed at supersonic engine exhaust noise reduction are demonstrating benefits of 3-4 dBA using passive methods to increase jet mixing and break up shock cells in over-expanded flows. While progress is being made, high speed jet noise continues to be a research challenge for small business jets and tactical military aircraft. The current work benchmarks high speed jet noise using laboratory scale jets for the purpose of a) identifying source and propagation mechanisms, and b) providing validation data for simulation/modeling methods. Laboratory scale experiments are presented over a Mach number range of M = 0.68 to 1.5 with static temperature ratio ranging from Tr = 0.68 to 2. A unique near field rotating phased microphone array technique was used to identify the large-scale turbulence structure noise source and Mach waves in supersonic shock-free jets. A companion paper documents the near field pressure statistics and projection of the convected wave packet to the far field. Validation against the directly measured far field levels quantitatively establishes the large scale structure noise contributions. The combined studies underpin a long term effort to develop modeling methods and new concepts for jet noise suppression based on controlling the evolution of the large-scale turbulence structures.

Item Type:Conference or Workshop Item (Paper)
Related URLs:
URLURL TypeDescription Paper Paper
Colonius, T.0000-0003-0326-3909
Additional Information:© 2008 by Robert H. Schlinker. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. Published Online: 4 Nov 2012. The authors gratefully acknowledge the support of NAVAIR and TTC Technologies Inc., the SBIR partner in this work.
Funding AgencyGrant Number
Naval Air Systems Command (NAVAIR)UNSPECIFIED
Subject Keywords:Aeroacoustics
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AIAA Paper2008-2890
Record Number:CaltechAUTHORS:20190717-102320761
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:97219
Deposited By: Melissa Ray
Deposited On:18 Jul 2019 22:07
Last Modified:16 Nov 2021 17:29

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