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Experimental hypersonic inlet investigation with application to dual-mode scramjet.Hypersonic inlet performance estimates used to predict thrust and fuel specific impulse possible with hydrogen fueled subsonic and supersonic combustion ramjets
Document ID
19650044095
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Karanian, A. J.
Kepler, C. E.
Date Acquired
August 2, 2013
Publication Date
June 1, 1965
Subject Category
Propulsion Systems
Report/Patent Number
AIAA PAPER 65-588
Report Number: AIAA PAPER 65-588
Accession Number
65A26799
Funding Number(s)
CONTRACT_GRANT: NASW-715
Distribution Limits
Public
Copyright
Other
Keywords
HYPERSONIC INLET
INLET FLOW
HYDROGEN FUEL
SUPERSONIC COMBUSTION RAMJET MISSILE

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