Temperature measurements were made, in supersonic nozzles with cone exit half-angles of 10.5 and 7°, for hydrogen air and methane air combustion products at stagnation temperatures up to 5400 R and pressures up to 4.5 atm; results indicate freezing in vicinity of nozzle throat; comparisons of data with approximate freezing point analysis and exact calculation showed good agreement with both; feasibility of spectroscopic concentration measurements shown; studies are carried out for hydrogen fueled subsonic combustion ramjet engines; Bray's criterion is used to determine nozzle freezingpoint; engine parameters such as nozzle throat size, throat radius of curvature, nozzle shape, Mach number, altitude, equivalence ratio, and inlet kinetic energy efficiency are varied to determine their effect on recombination and specific impulse; study shows that recombination losses are not serious for Mach numbers up to 9 and freestream dynamic pressures above 500 psf.
Effects of exhaust nozzle recombination of hypersonic ramjet performance
AIAA J
AIAA Journal ; 1 , n 9
1963
13 pages
Article (Journal)
English
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Effects of exhaust nozzle recombination on hypersonic ramjet performance -- 2
Engineering Index Backfile | 1963
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