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Simulation of Supersonic Jet Noise with the Adaptation of Overflow CFD Code and Kirchhoff Surface IntegralAn acoustic prediction capability for supersonic axisymmetric jets was developed on the basis of OVERFLOW Navier-Stokes CFD (Computational Fluid Dynamics) code of NASA Langley Research Center. Reynolds-averaged turbulent stresses in the flow field are modeled with the aid of Spalart-Allmaras one-equation turbulence model. Appropriate acoustic and outflow boundary conditions were implemented to compute time-dependent acoustic pressure in the nonlinear source-field. Based on the specification of acoustic pressure, its temporal and normal derivatives on the Kirchhoff surface, the near-field and the far-field sound pressure levels are computed via Kirchhoff surface integral, with the Kirchhoff surface chosen to enclose the nonlinear sound source region described by the CFD code. The methods are validated by a comparison of the predictions of sound pressure levels with the available data for an axisymmetric turbulent supersonic (Mach 2) perfectly expanded jet.
Document ID
20010094062
Acquisition Source
Kennedy Space Center
Document Type
Technical Memorandum (TM)
Authors
Kandula, Max (DYNACS Engineering Co., Inc. Cocoa Beach, FL United States)
Caimi, Raoul (NASA Kennedy Space Center Cocoa Beach, FL United States)
Steinrock, T.
Date Acquired
September 7, 2013
Publication Date
July 1, 2001
Subject Category
Acoustics
Report/Patent Number
NASA/TM-2001-210263
NAS 1.15:210263
Funding Number(s)
CONTRACT_GRANT: NAS10-98001
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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