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Measurements of Mean Static Pressure and Far Field Acoustics of Shock Containing Supersonic JetsThe far field acoustic data base generated in studies of broadband shock noise from supersonic jets is presented. Both conical and contoured nozzles of exit Mach numbers 1.0, 1.5, and 2.0 were tested using unheated air at pressure ratios ranging from 1.9 to 14. Tests were performed both with and without screech suppression tabs. Overall sound pressure variations and representative 1/3-octave and narrowband spectra are presented. The mean static pressure measured within these jets is also surveyed.
Document ID
19820025274
Document Type
Technical Memorandum (TM)
Authors
Norum, T. D. (NASA Langley Research Center Hampton, VA, United States)
Seiner, J. M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1982
Subject Category
ACOUSTICS
Report/Patent Number
L-15378
NAS 1.15:84521
NASA-TM-84521
Funding Number(s)
PROJECT: RTOP 505-32-03-05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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