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NACA 2414 (n2414-il)

NACA 2414 - NACA 2414 airfoil


Airfoil n2414-il
Details Dat file Parser  
(n2414-il) NACA 2414
NACA 2414 airfoil
Max thickness 14% at 29.5% chord.
Max camber 2% at 39.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 2414
 1.00000  0.00147
 0.99739  0.00210
 0.98929  0.00396
 0.97587  0.00700
 0.95729  0.01112
 0.93372  0.01620
 0.90542  0.02207
 0.87267  0.02857
 0.83582  0.03552
 0.79527  0.04274
 0.75143  0.05004
 0.70480  0.05723
 0.65586  0.06412
 0.60515  0.07053
 0.55324  0.07629
 0.50069  0.08120
 0.44808  0.08512
 0.39598  0.08787
 0.34454  0.08913
 0.29482  0.08866
 0.24740  0.08645
 0.20285  0.08255
 0.16169  0.07707
 0.12440  0.07014
 0.09141  0.06198
 0.06310  0.05281
 0.03977  0.04289
 0.02165  0.03245
 0.00892  0.02171
 0.00169  0.01085
 0.00000  0.00000
 0.00379 -0.01031
 0.01293 -0.01956
 0.02730 -0.02770
 0.04669 -0.03471
 0.07087 -0.04054
 0.09957 -0.04516
 0.13246 -0.04858
 0.16918 -0.05082
 0.20937 -0.05195
 0.25260 -0.05208
 0.29844 -0.05133
 0.34644 -0.04987
 0.39611 -0.04787
 0.44739 -0.04537
 0.49931 -0.04232
 0.55129 -0.03886
 0.60276 -0.03516
 0.65316 -0.03132
 0.70194 -0.02745
 0.74857 -0.02365
 0.79252 -0.01998
 0.83331 -0.01650
 0.87048 -0.01328
 0.90360 -0.01035
 0.93230 -0.00776
 0.95626 -0.00557
 0.97518 -0.00381
 0.98886 -0.00252
 0.99713 -0.00173
 1.00000 -0.00147
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Lednicer format dat file
Selig format dat file

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Polars for NACA 2414 (n2414-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   n2414-il50,000929.2 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n2414-il50,000532.7 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   n2414-il100,000947.8 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   n2414-il100,000548.1 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   n2414-il200,000965.1 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n2414-il200,000562.1 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   n2414-il500,000987.6 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   n2414-il500,000579.4 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   n2414-il1,000,0009103.7 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   n2414-il1,000,000590 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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