Experimental Evaluation of Various Nonmetallic Ablative Materials as Nozzle Sections of Hydrogen-Oxygen Rocket Engine.
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION CLEVELAND OH LEWIS RESEARCH CEN TER
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An investigation was conducted to evaluate 40 nonmetallic ablative materials as the nozzle section of a 150-pound-nominal-thrust, gaseous-hydrogen - liquid-oxygen rocket engine operating at an initial nominal chamber pressure of 100 pounds per square inch absolute, a throat diameter of 1.2 inches, and an oxidant-fuel ratio of approximately 6.7. These commercially available materials were either nonreinforced or reinforced with woven cloths such as silica, graphite, carbon, or asbestos and with phenolic or epoxy resins. The results, which were obtained with an engine operating with a c efficiency of approximately 93 percent and therefore not representative of a high performance system, were used only for comparative purposes. The results of this study are presented as a rating of materials based on nozzle throat erosion and weight loss. The best erosion resistance was obtained with silica cloth reinforced materials containing either polyamide modified phenolic or phenolic with silica powder filler. No correlation between erosion rate and char depth was obtained. The combustion efficiency of the test engine, as would be expected, influenced the nozzle erosion rate.
- Ceramics, Refractories and Glass
- Rocket Engines