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Modeling of vortex generated sound in solid propellant rocket motorsThere is considerable evidence based on both full scale firings and cold flow simulations that hydrodynamically unstable shear flows in solid propellant rocket motors can lead to acoustic pressure fluctuations of significant amplitude. Although a comprehensive theoretical understanding of this problem does not yet exist, procedures were explored for generating useful analytical models describing the vortex shedding phenomenon and the mechanisms of coupling to the acoustic field in a rocket combustion chamber. Since combustion stability prediction procedures cannot be successful without incorporation of all acoustic gains and losses, it is clear that a vortex driving model comparable in quality to the analytical models currently employed to represent linear combustion instability must be formulated.
Document ID
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Flandro, G. A.
(Utah Univ. Salt Lake City, UT, United States)
Date Acquired
August 11, 2013
Publication Date
November 1, 1980
Publication Information
Publication: NASA. Langley Research Center The 17th JANNAF Combust. Meeting, Vol. 1
Subject Category
Propellants And Fuels
Accession Number
Funding Number(s)
CONTRACT_GRANT: F04701-77-C-0060
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