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High-pressure calorimeter chamber tests for liquid oxygen/kerosene (LOX/RP-1) rocket combustionAn experimental program was conducted to investigate the rocket combustion and heat transfer characteristics of liquid oxygen/kerosene (LOX/RP-1) mixtures at high chamber pressures. Two water-cooled calorimeter chambers of different combustion lengths were tested using 37- and 61-element oxidizer-fuel-oxidizer triplet injectors. The tests were conducted at nominal chamber pressures of 4.1, 8.3, and 13.8 MPa abs (600, 1200, and 2000 psia). Heat flux Q/A data were obtained for the entire calorimeter length for oxygen/fuel mixture ratios of 1.8 to 3.3. Test data at 4.1 MPa abs compared favorably with previous test data from another source. Using an injector with a fuel-rich outer zone reduced the throat heat flux by 47 percent with only a 4.5 percent reduction in the characteristic exhaust velocity efficiency C* sub eff. The throat heat transfer coefficient was reduced approximately 40 percent because of carbon deposits on the chamber wall.
Document ID
Document Type
Technical Publication (TP)
Masters, Philip A.
(NASA Lewis Research Center Cleveland, OH, United States)
Armstrong, Elizabeth S.
(NASA Lewis Research Center Cleveland, OH, United States)
Price, Harold G.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 5, 2013
Publication Date
December 1, 1988
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
NAS 1.60:2862
Accession Number
Funding Number(s)
PROJECT: RTOP 582-01-11
Distribution Limits
Work of the US Gov. Public Use Permitted.
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