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The scaling of the threshold conditions for solid propellant erosive burningRocket test firings were performed to measure the transition length threshold conditions while systematically varying various rocket motor parameters. These include the crossflow velocity, the chamber pressure, the propellant nonerosive burning rate, the propellant surface roughness, and the motor port diameter. The erosive burning trends with varying propellant burning rate, motor chamber pressure, and mass flow rate are consistent with published results.
Document ID
19880060819
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Strand, L. D.
(Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Nguyen, M. H.
(California Institute of Technology Jet Propulsion Laboratory, Pasadena, United States)
Cohen, N. S.
(Cohen Professional Services, Inc. Redlands, CA, United States)
Date Acquired
August 13, 2013
Publication Date
July 1, 1988
Subject Category
Propellants And Fuels
Report/Patent Number
AIAA PAPER 88-3254
Accession Number
88A48046
Distribution Limits
Public
Copyright
Other

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