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Characteristics of the NACA 23012 Airfoil from Tests in the Full-Scale and Variable-Density TunnelsThis report gives the results of tests in the NACA full-scale and variable-density tunnels of a new wing section, the NACA 23012, which is one of the more promising of an extended series of related airfoils recently developed. The tests were made at several values of the Reynolds number between 1,000,000 and 8,000,000. The new airfoil develops a reasonably high maximum lift and a low profile drag, which results in an unusually high value of the speed-range index. In addition, the pitching-moment coefficient is very small. The superiority of the new section over well-known and commonly used sections of small camber and moderate thickness is indicated by making a direct comparison with variable-density tests of the NACA 2212, the well-known NACA family airfoil that most nearly resembles it. The superiority is further indicated by comparing the characteristics with those obtained from full-scale-tunnel tests of the Clark y airfoil.
Document ID
19930091603
Document Type
Other
Authors
Jacobs, Eastman N
Clay, William C
Date Acquired
September 6, 2013
Publication Date
January 1, 1936
Report/Patent Number
NACA-TR-530
Accession Number
93R20893
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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