Calculated data for the combustion with liquid oxygen of water-diluted alcohols and paraffin in rocket motors

dc.contributor.author	I. C. Hutcheon	en_US
dc.contributor.author	S. W. Green	en_US
dc.date.accessioned	2014-10-21T15:50:10Z
dc.date.available	2014-10-21T15:50:10Z
dc.date.issued	1947	en_US
dc.identifier.other	ARC/R&M-2572	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/2888
dc.description.abstract	Flame compositions, combustion temperatures, and specific impulses have been calculated for the combustion with liquid oxygen of (1) methyl alcohol with varying additions of water, (2) ethyl alcohol with varying additions of water, (3) aviation turbine paraffin. Calculations have been confined to propellant combinations with an excess of alcohol or paraffin and which produce combustion temperatures below about 2,700 deg K. An expansion ratio of 20:1 has been assumed in obtaining the specific impulses, and the methods of calculation are fully explained. The various propellant combinations are assessed from several points of view as to their usefulness for rocket propulsion.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Calculated data for the combustion with liquid oxygen of water-diluted alcohols and paraffin in rocket motors	en_US