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Aeroacoustic Data for a High Reynolds Number Axisymmetric Subsonic JetThe near field fluctuating pressure and aerodynamic mean flow characteristics of a cold subsonic jet issuing from a contoured convergent nozzle are presented. The data are presented for nozzle exit Mach numbers of 0.30, 0.60, and 0.85 at a constant jet stagnation temperature of 104 F. The fluctuating pressure measurements were acquired via linear and semi-circular microphone arrays and the presented results include plots of narrowband spectra, contour maps, streamwise/azimuthal spatial correlations for zero time delay, and cross-spectra of the azimuthal correlations. A pitot probe was used to characterize the mean flow velocity by assuming the subsonic flow to be pressure-balanced with the ambient field into which it exhausts. Presented are mean flow profiles and the momentum thickness of the free shear layer as a function of streamwise position.
Document ID
19990047088
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Ponton, Michael K.
(NASA Langley Research Center Hampton,VA United States)
Ukeiley, Lawrence S.
(NASA Langley Research Center Hampton,VA United States)
Lee, Sang W.
(Joint Inst. for Advancement of Flight Sciences Hampton, VA United States)
Date Acquired
September 6, 2013
Publication Date
May 1, 1999
Subject Category
Acoustics
Report/Patent Number
L-17870
NASA/TM-1999-209336
NAS 1.15:209336
Funding Number(s)
PROJECT: RTOP 522-32-31-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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