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Hypersonic research engine project. Phase 2: Aerothermodynamic integration model developmentThe analytical effort was directed towards (1) completing the design of the combustor exit instrumentation assembly, (2) analyzing the coolant flow distribution of the cowl leading edge tip section, (3) determining effects of purge gas pressure on AIM performance analysis, and (4) analyzing heat transfer and associated stress problems related to the cowl leading edge tip section and the nozzle shroud assembly for test conditions.
Document ID
19720018063
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Jilly, L. F. (AiResearch Mfg. Co. Los Angeles, CA, United States)
Date Acquired
August 6, 2013
Publication Date
October 15, 1970
Subject Category
Propulsion Systems
Report/Patent Number
NASA-CR-112058
AP-70-6800
ITDR-10
Report Number: NASA-CR-112058
Report Number: AP-70-6800
Report Number: ITDR-10
Accession Number
72N25713
Funding Number(s)
CONTRACT_GRANT: NAS1-6666
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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