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Cold flow investigation of a low angle turbojet plug nozzle with fixed throat and translating shroud at Mach numbers from 0 to 2.0Cold flow tests of aerodynamic characteristics of plug nozzle configuration for turbojet engines operating at supersonic speeds
Document ID
19680020481
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Bresnahan, D. L. (NASA Lewis Research Center Cleveland, OH, United States)
Johns, A. L. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
August 1, 1968
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TM-X-1619
Report Number: NASA-TM-X-1619
Accession Number
68N29953
Funding Number(s)
CONTRACT_GRANT: 720-03-01-08-22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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