NASA NTRS · 19810014651
Advanced oxygen-hydrocarbon rocket engine study
Abstract
The program consists of parametric analysis and design to provide a consistent engine system data base for defining advantages and disadvantages, system performance and operating limits, engine parametric data, and technology requirements for candidate high pressure LO2/Hydrocarbon engine systems. The parametric chamber and nozzle cooling analysis was completed for the four potential coolants: RP-1, LCH4, LO2, and LH2. A summary of the cooling capability of each propellant is presented.
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Obrien, J. O., Ewen, R. L., Kent, S., Meagher, G. M.. 1980-04-10. Advanced oxygen-hydrocarbon rocket engine study. https://ntrs.nasa.gov/citations/19810014651
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