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Langley Full-scale-tunnel Investigation of the Fuselage Boundary Layer on a Typical Fighter Airplane with a Single Liquid-cooled Engine
Document ID
19930081705
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Czarnecki, K R
Pasamanick, Jerome
Date Acquired
August 16, 2013
Publication Date
June 1, 1946
Report/Patent Number
NACA-TN-1087
Accession Number
93R10995
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
BOUNDARY LAYER THICKNESS
BOUNDARY LAYER - FUSELAGES
ENGINES, LIQUID-COOLED
AIRPLANES, FIGHTER

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