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Effects of wing-fuselage flow fields on missile loads at subsonic speedsSwept wing-fuselage flow fields on missile loads at subsonic speeds
Document ID
19660024024
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Alford, W. J., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
June 27, 1955
Subject Category
Aircraft
Report/Patent Number
NACA-RM-L55E10A
Accession Number
66N33314
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
FLOW FIELD
SWEPT WING
MISSILE
WING-FUSELAGE COMBINATION
SUBSONIC SPEED

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