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Minimum Drag of Four Versions of a Swept-wing Fighter Airplane Obtained from Flight Tests of Rocket-boosted Models at Mach Numbers from 0.81 to 1.71Swept wing fighter aircraft drag coefficient reduction by configuration redesign
Document ID
19660024810
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Hastings, E. C., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
September 7, 1956
Subject Category
Aircraft
Report/Patent Number
NACA-RM-L56E25A
Accession Number
66N34100
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
AIRCRAFT CONFIGURATION
DRAG COEFFICIENT
FIGHTER AIRCRAFT
SWEPT WING

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