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Hypersonic research engine project. Phase 2: Aerothermodynamic Integration Model (AIM) test reportThe Hypersonic Research Engine-Aerothermodynamic Integration Model (HRE-AIM) was designed, fabricated, and tested in the Hypersonic Tunnel Facility. The HRE-AIM is described along with its installation in the wind tunnel facility. Test conditions to which the HRE-AIM was subjected and observations made during the tests are discussed. The overall engine performance, component interaction, and ignition limits for the design are evaluated.
Document ID
19750018941
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Andersen, W. L. (AiResearch Mfg. Co. Torrance, CA, United States)
Kado, L. (AiResearch Mfg. Co. Torrance, CA, United States)
Date Acquired
September 3, 2013
Publication Date
May 19, 1975
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
NASA-CR-132655
AIRESEARCH-74-10784
Report Number: NASA-CR-132655
Report Number: AIRESEARCH-74-10784
Accession Number
75N27013
Funding Number(s)
CONTRACT_GRANT: NAS1-6666
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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