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.
