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A numerical analysis of the use of perforated walls to control shock location and movement in an internal compression supersonic inletNumerical analysis of shock control by using perforated walls in internal compression supersonic inlets
Document ID
19690022960
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Report (TR)
Authors
Matthews, C. W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
July 1, 1969
Subject Category
Aerodynamics
Report/Patent Number
NASA-TR-R-317
Report Number: NASA-TR-R-317
Accession Number
69N32338
Funding Number(s)
CONTRACT_GRANT: 720-03-00-02-23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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