Experimental combustion efficiencies of 11 different propellant combinations were determined in nominal 200 lb thrust rocket engine at three chamber lengths and compared with analytical results; data agreed with predicted results except for hydrazine, which may have decomposed in liquid phase, and ammonia-fluorine.
Propellant vaporization as criterion for rocket-engine design -- Experimental performance, vaporization, and heat-transfer rates with various propellant combinations
NASA -- Memo
National Aeronautics and Space Administration -- Memorandums ; Memo n 12-29-58E
1959
31 pages
Report
Englisch
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