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Hypersonic research engine/aerothermodynamic integration model, experimental results. Volume 1: Mach 6 component integrationThe NASA Hypersonic Research Engine (HRE) Project was initiated for the purpose of advancing the technology of airbreathing propulsion for hypersonic flight. A large component (inlet, combustor, and nozzle) and structures development program was encompassed by the project. The tests of a full-scale (18 in. diameter cowl and 87 in. long) HRE concept, designated the Aerothermodynamic Integration Model (AIM), at Mach numbers of 5, 6, and 7. Computer program results for Mach 6 component integration tests are presented.
Document ID
19760016176
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-72821
Report Number: NASA-TM-X-72821
Accession Number
76N23264
Funding Number(s)
CONTRACT_GRANT: NAS1-6666
PROJECT: RTOP 505-05-41-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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