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Effects of Mach Number up to 0.34 and Reynolds Number up to 8 X 10(exp 6) Power on the Maximum Lift Coefficient of a Wing of NACA 66-series Airfoil Sections
Document ID
19930082891
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Furlong, G Chester
Fitzpatrick, James E
Date Acquired
August 16, 2013
Publication Date
December 1, 1950
Report/Patent Number
NACA-TN-2251
Report Number: NACA-TN-2251
Accession Number
93R12181
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
REYNOLDS NUMBER
MACH NUMBER
WIND TUNNEL TESTS - NACA - PRESSURE (19 FEET)
FLAPS, TRAILING EDGE - COMPLETE WINGS
AIRFOILS - NACA 66(215)-116(A=0 6) - 66(215)-216(A=0 6)
LIFT COEFFICIENTS - WINGS
WING FLAPS, SPLIT
CHORDWISE
FLOW, VISCOUS
REYNOLDS NUMBER EFFECTS - COMPLETE WINGS
SURFACE CONDITIONS - COMPLETE WINGS
PRESSURE DISTRIBUTION - WINGS
FLOW, SUBSONIC
AIRFOIL SURFACES - ROUGHNESS
WING FLAPS, SPLIT

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