Study to determine local values of heat flux in rocket engine thrust chambers that incorporated convergent divergent nozzles of 2 different geometries; largest nozzle expansion area ratio investigated was 20 to 1; chamber pressures ranged from 100 to 300 psia at thrust levels between 1000 and 5000 lb-ft; propellants used were nitrogen tetroxide and hydrazine at nominal mixture ratio of 1.0.
Experimental investigation of heat transfer rates in rocket thrust chambers
AIAA J
AIAA Journal ; 1 , n 2
1963
9 pages
Aufsatz (Zeitschrift)
Englisch
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