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Hypersonic research engine/aerothermodynamic integration model, experimental results. Volume 2: Mach 6 performanceComputer program performance results of a Mach 6 hypersonic research engine during supersonic and subsonic combustion modes were presented. The combustion mode transition was successfully performed, exit surveys made, and effects of altitude, angle of attack, and inlet spike position were determined during these tests.
Document ID
19760020150
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Andrews, E. H., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Mackley, E. A.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
April 1, 1976
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-TM-X-72822
Accession Number
76N27238
Funding Number(s)
PROJECT: RTOP 505-05-41-03
CONTRACT_GRANT: NAS1-6666
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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