The effects of oxidizer injector design on hybrid rockets combustion stability

Collection of Technical Papers - AIAA/ASME/SAE/ASEE 42nd Joint Propulsion Conference

Volumn 5, Issue , 2006, Pages 3548-3563

  Carmicino, C ^a,b,c   Sorge, A Russo ^a,b,c  

^a UNIVERSITY OF NAPLES FEDERICO II   (Italy)

^b Department of Space Science and Engineering L G Napolitano ^*  (Italy)

^c AIAA   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

GASEOUS OXYGEN; HYBRID ROCKETS; OXIDIZER INJECTOR; PRESSURE SPECTRA;

BOUNDARY LAYERS; FUELS; NOZZLES; OXYGEN; PRESSURE EFFECTS; ROCKET ENGINES; THERMAL EFFECTS;

COMBUSTION;

EID: 34249072500     PISSN: None     EISSN: None     Source Type: Conference Proceeding    
DOI: None     Document Type: Conference Paper

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