Uncooled rocket engine was investigated over chamber pressure from 45 to 300 psia and oxidant-fuel ratio from 2 to 7; combustion dead times were calculated from chamber-pressure frequency measurements; dead time decreased with increased chamber pressure at constant oxidant-fuel ratio or liquid-oxygen injection velocity; close agreement obtained between measured dead times and those calculated from frequency measurements.
Relations of combustion dead time to engine variables for 20,000-pound-thrust gaseous-hydrogen-liquid-oxygen rocket engine
NASA -- Tech Note
1961
23 pages
Report
English
© Metadata Copyright Elsevier B. V. All rights reserved.