Experimental Evaluation of Six Ablative-material Thrust Chambers as Components of Storable-propellant Rocket Engines |
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470 seconds 600 Accumulative ablative material ablative-material chamber section ablative-material thrust chambers accumulative firing Aerozine 50 altitude chamber cham chamber pressure char thickness Characteristic velocity efficiency combustion performance level configurations contoured throat Cross section diameter Dimensional elastomer additive End of firing erosion occurred fiber fiber-orientation angle flat wrap layer flow coefficient fuel graphite-cloth increase in throat Injector-face chamber injector-face pressure inner layer material of chamber Micrometer mil per second mil/sec mm/sec minimum point minor firings nitrogen tetroxide nominally nozzle nozzle throat outer flat wrap overall erosion rate oxidant oxidant-to-fuel ratio percent area change phenolic resin psia 689 kN/mē radius and percent ratio distribution ratio of 2.0 reduction in throat reinforcement and phenolic results for chamber run tank seconds of accumulative section of chamber shown in figure six ablative-material thrust test chamber throat erosion Throat radius change throat region thrust coefficient efficiency tubular throat Water-cooled section