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EFFECTS OF EXHAUST NOZZLE RECOMBINATION ON HYPERSONIC RAMJET PERFORMANCE. I - EXPERIMENTAL MEASUREMENTSTemperature measurements in supersonic nozzles for hydrogen-air and methane-air combustion products at stagnation temperatures up to 5,400 degrees rankine and pressures up to 4.5 atmospheres
Document ID
19630026662
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Franciscus, L. C.
Lezberg, E. A.
Date Acquired
August 1, 2013
Publication Date
September 1, 1963
Subject Category
Aircraft
Accession Number
63A22721
Distribution Limits
Public
Copyright
Other
Keywords
NOZZLE FLOW
EXHAUST NOZZLE
COMBUSTION TEMPERATURE
SUPERSONIC NOZZLE

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