Results from test program which evaluated heat transfer characteristics of ejector systems that turned rocket exhaust gases through 90° show differences in thermal behavior that can be obtained during turning of gases; maximum heating rate was reduced by factor of seven when ejector had long radius, as compared to short radius 90° turn and by factor of five by permitting gases to shock down to subsonic flow prior to entering short radius bend; method of converting scale-model heat-transfer coefficient data to any other scale size, working fluid, nozzle chamber temperature or chamber pressure and empirical correlation of maximum heating rates is presented.
Heat transfer investigation of ejector systems with 90° turns
AIAA -- Tech Paper
AIAA -- Space Simulation Testing Conference ; 1964 Heat problems
1964
6 pages
Conference paper
English
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Calculation of Aerodynamic Performance and Heat Transfer of an Ejector Nozzle
British Library Conference Proceedings | 1994
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