Studies are carried out for hydrogen-fueled subsonic combustion ramjet engines; Bray's criterion is used to determine nozzle freezing point; nozzle performance is calculated by assuming equilibrium conditions up to freezing point and frozen flow from freezing point to nozzle exit; parameters include nozzle throat size, throat radius of curvature, nozzle shape, Mach number, altitude, equivalence ratio, and inlet kinetic energy efficiency; it is shown that recombination losses are not expected to be serious for Mach numbers up to 9 and free-stream dynamic pressures above 500 psf.
Effects of exhaust nozzle recombination on hypersonic ramjet performance -- 2
AIAA-ASME -- Paper
AIAA-ASME Hypersonic Ramjet Conference ; 1963 Combustion
1963
12 pages
Conference paper
English
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Effects of exhaust nozzle recombination of hypersonic ramjet performance
Engineering Index Backfile | 1963
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