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Carbon monoxide and oxygen combustion experiments: A demonstration of Mars in situ propellantsThe feasibility of using carbon monoxide and oxygen as rocket propellants was examined both experimentally and theoretically. The steady-state combustion of carbon monoxide and oxygen was demonstrated for the first time in a subscale rocket engine. Measurements of experimental characteristic velocity, vacuum specific impulse, and thrust coefficient efficiency were obtained over a mixture ratio range of 0.30 to 2.0 and a chamber pressures of 1070 and 530 kPa. The theoretical performance of the propellant combination was studied parametrically over the same mixture ratio range. In addition to one dimensional ideal performance predictions, various performance reduction mechanisms were also modeled, including finite-rate kinetic reactions, two-dimensional divergence effects and viscous boundary layer effects.
Document ID
Document Type
Conference Paper
Linne, Diane L.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1991
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
AIAA PAPER 91-2443
NAS 1.15:104473
Meeting Information
Joint Propulsion Conference(Sacramento, CA)
Accession Number
Funding Number(s)
PROJECT: RTOP 506-42-72
Distribution Limits
Work of the US Gov. Public Use Permitted.
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