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Preliminary study of effects of Reynolds number and boundary-layer transition location on shock-induced separationTransonic wind tunnel studies on airfoil to determine effects of Reynolds number and boundary layer transition location on shock induced separated flow
Document ID
19690006789
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Blackwell, J. A., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
January 1, 1969
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-5003
Report Number: NASA-TN-D-5003
Meeting Information
Meeting: SPECIALISTS'' MEETING ON TRANSONIC AERODYN., AGARD
Location: PARIS
Start Date: September 1, 1968
Sponsors: AGARD
Accession Number
69N16121
Funding Number(s)
CONTRACT_GRANT: 126-13-01-67-23
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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