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An Elementary Calculation for the Burning Rate of Composite Solid Propellants

Culick, F. E. C. and Dehority, G. L. (1969) An Elementary Calculation for the Burning Rate of Composite Solid Propellants. Combustion Science and Technology, 1 (3). pp. 193-204. ISSN 0010-2202. doi:10.1080/00102206908952200.

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A calculation of the burning rate for a composite solid propellant is based on a model in which the distribution of combustion in the gas phase is specified. The formulation of the problem can accommodate an arbitrary distribution, but only the simplest case of uniform combustion is treated here. An inverse numerical computation is carried out, as the magnitude of the reaction rate, and its dependence on pressure, are calculated for several specified burning rates. Simultaneously, flame stand-off distances and thicknesses are determined as part of the solution. The numerical results for those characteristics of the flame appear to be comparable to observed values. However, the principal value of this treatment of the problem is due to the ease with which one can study and understand the influence of the various physical properties and combustion characteristics.

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Additional Information:© 1969 Gordon and Breach, Science Publishers Ltd. Received August 18, 1969. This work was supported by NOSC Task Assignment ORD-331-002/200-1/UF19-332-303. The senior author is a consultant to the Aerothermochemistry Division of the Naval Weapons Center.
Group:Guggenheim Jet Propulsion Center, GALCIT
Funding AgencyGrant Number
Navy Operational Support Center (NOSC)ORD-331-002/200-1/UF19-332-303
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Guggenheim Jet Propulsion CenterUNSPECIFIED
Issue or Number:3
Record Number:CaltechAUTHORS:20101221-134757282
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:21485
Deposited By: Ruth Sustaita
Deposited On:21 Dec 2010 22:17
Last Modified:09 Nov 2021 15:57

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