A study of injection processes for liquid oxygen and gaseous hydrogen in a 200-pound-thrust rocket engine Page: 3 of 34
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NACA RM E56125a
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
RESEARCH MEMORANDUM
A STUDY OF INJECTION PROCESSES FOR LIQUID OXYGEN AND GASEOUS
o
0 HYDROGEN IN A 200-POUND-TERUST ROCKET ENGINE
By Carmon M. Auble
SUMMARY
Six single-element injectors that systematically varied propellant
spreading and mixing were compared using liquid oxygen and gaseous hydro-
gen in a 200-pound-thrust rocket engine. Characteristic velocity was
measured over a range of oxidant-fuel weight ratios of approximately 2
to 7 at a total propellant flow of about 0.6 pound per second. Most of
the experiments were made with propellants at an initial temperature of
-320 F.
Characteristic velocity efficiency for all the injectors, except
the parallel jets, approached 94 to 97 percent at the extreme fuel-rich
mixture ratio. Injectors that mixed and spread the propellants had ef-
ficiencies exceeding 93 percent over the entire mixture range. An in-
crease in hydrogen temperature from -3200 to 800 F increased efficiency
about 20 percent. For similar propellant treatment the combustor length
for oxygen-hydrogen was about 0.2 to 0.5 times that needed to obtain
comparable efficiencies with oxygen-heptane.
Fuel dispersion increased efficiency only slightly more than oxygen
dispersion at comparable conditions. In both cases, the increase varied
with mixture ratio and the treatment of the other propellant. Mixing
had a relatively small effect on efficiency over the entire mixture
range.
The data were compared with previous results for heptane-oxygen,
and it was deduced that the combustion rates of both systems are con-
trolled by physical processes such as atomization, evaporation, and dif-
fusion, rather than by chemical kinetics.
INTRODUCTION
The oxygen-hydrogen propellant combination is of interest for long-
range rocket missiles because of its high theoretical specific impulses
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Auble, Carmon M. A study of injection processes for liquid oxygen and gaseous hydrogen in a 200-pound-thrust rocket engine, report, January 9, 1957; (https://digital.library.unt.edu/ark:/67531/metadc62839/m1/3/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.