Experimental evaluation of six ablative-material thrust chambers as components of storable-propellant rocket engines
National Aeronautics and Space Administration, 1967 - Technology & Engineering - 41 pages
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470 seconds ablative material ablative-material chamber section ablative-material thrust chambers altitude chamber cham chamber pressure char thickness Characteristic velocity efficiency combustion performance level COMPONENTS OF STORABLE-PROPELLANT contoured throat Dimensional elastomer additive erosion occurred experimental fiber fiber-orientation angle flat wrap layer flow coefficient flow equation fuel full-length ablative chambers graphite-cloth high-silica-cloth reinforcement increase in throat injector-face pressure inner layer material of chamber micrometer mil per second mil/sec minor firings mm/sec nitrogen tetroxide nominally nozzle nozzle throat outer flat wrap overall erosion rate oxidant oxidant-to-fuel ratio percent area change phenolic resin phenolic-resin material psia 12 kN/m psia N/m radius and percent ratio distribution reduction in throat reinforcement and phenolic results for chamber seconds of accumulative section of chamber shown in figure Silica silica-cloth six ablative-material thrust steel heat-sink chambers streaking and gouging test chamber throat erosion throat radius throat region throat-erosion resistance throat-radius change thrust coefficient efficiency tubular throat