Evaluation of Three Injectors in a 2400-Pound-Thrust Rocket Engine Using Liquid Oxygen and Liquid Ammonia
Description:
Report presenting the performance of three injector types in a 2400-pound-thrust rocket test chamber. Characteristic velocity and specific impulses were obtained over a range of oxidant-to-fuel ratios at a nominal chamber pressure of 600 pounds per square inch absolute. RMI-1 and 2 had fairly similar results, but RMI-3 gave no stabilized data due to combustion instability.
Date:
July 28, 1958
Creator:
Hendricks, Robert C.; Ehlers, Robert C. & Humphrey, Jack C.
Item Type:
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Partner:
UNT Libraries Government Documents Department