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Combustion performance and heat transfer characterization of LOX/hydrocarbon type propellants, volume 1A program to evaluate liquid oxygen and various hydrocarbon fuel as low cost alternative propellants suitable for future space transportation system applications is discussed. The emphasis of the program is directed toward low earth orbit maneuvering engine and reaction control engine systems. The feasibility of regeneratively cooling an orbit maneuvering thruster was analytically determined over a range of operating conditions from 100 to 1000 psia chamber pressure and 1000 to 10,000-1bF thrust, and specific design points were analyzed in detail for propane, methane, RP-1, ammonia, and ethanol; similar design point studies were performed for a filmcooled reaction control thruster. Heat transfer characteristics of propate were experimentally evaluated in heated tube tests. Forced convection heat transfer coefficients were determined over the range of fluid conditions encompassed by 450 to 1800 psia, -250 to +250 F, and 50 to 150 ft/sec, with wall temperatures from ambient to 1200 F. Seventy-seven hot firing tests were conducted with LOX/propane and LOC/ethanol, for a total duration of nearly 1400 seconds, using both heat sink and water-cooled calorimetric chambers.
Document ID
19840003251
Document Type
Contractor Report (CR)
Authors
Michel, R. W. (Aerojet Liquid Rocket Co. Sacramento, CA, United States)
Date Acquired
September 4, 2013
Publication Date
April 1, 1983
Subject Category
PROPELLANTS AND FUELS
Report/Patent Number
REPT-15958-MA-129T-003F-VOL-1
NASA-CR-171713
NAS 1.26:171713
Funding Number(s)
CONTRACT_GRANT: NAS9-15958
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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