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A modification to thin-airfoil-section theory, applicable to arbitrary airfoil sections, to account for the effects of thickness on the lift distribution
Document ID
19930082957
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Graham, David
Date Acquired
August 29, 2013
Publication Date
February 1, 1951
Report/Patent Number
NACA-TN-2298
Report Number: NACA-TN-2298
Accession Number
93R12247
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
AIRFOILS, CAMBERED
ANGLE OF ATTACK
LIFT DISTRIBUTION - AIRFOILS
AIRFOILS - NACA 631 012 - CHARACTERISTICS
THEORIES - AIRFOILS, THIN
VORTICES - AIRFOILS
AIRFOILS - NACA 64A810 (A=0 8) (MOD ) - CHARACTERISTICS
AIRFOILS - THICKNESS
AIRFOILS - NACA 0018 - CHARACTERISTICS
AIRFOILS - NACA 0010-63 (C1I=0 8) (MOD ) (A=0 8) - CHARACTERISTICS

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