Analysis defining thrust effectiveness obtained by oxidizer injection into fuel-rich exhaust products in divergent section of nozzle; concept could be applied to liquid bipropellant system that yields stoichiometric temperature of reaction products too high to be tolerated in region of nozzle throat; stoichiometric temperature of reaction products could be attained in divergent section of nozzle where convective heating is less severe than at throat; results obtained from flow model indicate greater increase in nozzle thrust by oxidizer injection in nozzle exit cone than by same propellant mass addition in combustion chamber.
Thrust effectiveness of oxidizer injection in convergent-divergent nozzle
AIAA J
AIAA Journal ; 2 , n 8
1964
3 pages
Aufsatz (Zeitschrift)
Englisch
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Convergent-divergent nozzle flows
Engineering Index Backfile | 1968
|Convergent-divergent nozzle flows.
AIAA | 1968
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