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Near-Field and Far-Field Noise Surveys of Solid-Fuel Rocket Engines for a Range of Nozzle Exit PressuresMeasurements of near- and far-field noise pressures are presented for a 1,500-pound-thrust engine and for several 5,000-pound-thrust engines for which the nozzle exit pressure was changed systematically in order to study its effects on the noise level and spectra. Near-field surveys indicated that the highest noise pressure occurred at about 20 exit diameters downstream if the nozzle near the transition from super-sonic to subsonic flow. The acoustical power radiated from all engines averaged about 0.5 percent of the mechanical power of the exhaust stream, the least noise being radiated by the nozzle having an exit pressure less than atmospheric. The rocket engines of these tests radiate more power per cycle at the lower frequencies than arte reported for subsonic jets in other related studies.
Document ID
Acquisition Source
Langley Research Center
Document Type
Other - NASA Technical Note (TN)
Mayes, William H.
(NASA Langley Research Center Hampton, VA, United States)
Lanford, Wade E.
(NASA Langley Research Center Hampton, VA, United States)
Hubbard, Harvey H.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
August 1, 1959
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
Accession Number
Distribution Limits
Work of the US Gov. Public Use Permitted.
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