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NACA 2408 (naca2408-il)

NACA 2408 - NACA 2408 airfoil


Airfoil naca2408-il
Details Dat file Parser  
(naca2408-il) NACA 2408
NACA 2408 airfoil
Max thickness 8% at 29.9% chord.
Max camber 2% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 2408
1.00000     0.00084
0.95033     0.00855
0.90054     0.01575
0.80078     0.02858
0.70081     0.03942
0.60068     0.04820
0.50039     0.05473
0.40000     0.05869
0.29900     0.05875
0.24852     0.05677
0.19809     0.05320
0.14778     0.04776
0.09768     0.03987
0.07273     0.03471
0.04794     0.02829
0.02337     0.01944
0.01128     0.01380
0.00000     0.00000
0.01372     -0.01134
0.02663     -0.01493
0.05206     -0.01891
0.07727     -0.02111
0.10232     -0.02237
0.15222     -0.02338
0.20191     -0.02320
0.25148     -0.02239
0.30100     -0.02125
0.40000     -0.01869
0.49961     -0.01585
0.59932     -0.01264
0.69919     -0.00942
0.79922     -0.00636
0.89946     -0.00353
0.94967     -0.00217
1.00000     -0.00084
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Selig format dat file

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Polars for NACA 2408 (naca2408-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca2408-il50,000937.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2408-il50,000536.7 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2408-il100,000952.6 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2408-il100,000548.9 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2408-il200,000966.6 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2408-il200,000558.9 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2408-il500,000980.6 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2408-il500,000567.5 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2408-il1,000,000986.8 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2408-il1,000,000582.1 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
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