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Dynamic response of a Mach 2.5 axisymmetric inlet with engine or cold pipe and utilizing 60 percent supersonic internal area contractionDynamic response of supersonic mixed compression inlet coupled to cold pipe or turbojet engine
Document ID
19690021958
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Wasserbauer, J. F. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 2, 2013
Publication Date
July 1, 1969
Subject Category
Propulsion Systems
Report/Patent Number
NASA-TN-D-5338
Report Number: NASA-TN-D-5338
Accession Number
69N31336
Funding Number(s)
CONTRACT_GRANT: 126-15-02-11-22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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