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NACA 1408 (naca1408-il)

NACA 1408 - NACA 1408 airfoil


Airfoil naca1408-il
Details Dat file Parser  
(naca1408-il) NACA 1408
NACA 1408 airfoil
Max thickness 8% at 30% chord.
Max camber 1% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 1408
1.00000     0.00084
0.95016     0.00698
0.90027     0.01271
0.80039     0.02305
0.70041     0.03193
0.60034     0.03931
0.50020     0.04502
0.40000     0.04869
0.29950     0.04939
0.24926     0.04819
0.19904     0.04574
0.14889     0.04171
0.09883     0.03558
0.07386     0.03138
0.04896     0.02602
0.02418     0.01862
0.01189     0.01324
0.00000     0.00000
0.01311     -0.01200
0.02582     -0.01620
0.05104     -0.02134
0.07614     -0.02458
0.10117     -0.02682
0.15111     -0.02953
0.20096     -0.03074
0.25074     -0.03101
0.30050     -0.03063
0.40000     -0.02869
0.49980     -0.02556
0.59966     -0.02153
0.69959     -0.01693
0.79961     -0.01193
0.89973     -0.00659
0.94984     -0.00378
1.00000     -0.00084
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Selig format dat file

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Polars for NACA 1408 (naca1408-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca1408-il50,000932.3 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1408-il50,000531.5 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1408-il100,000944.2 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1408-il100,000540.7 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1408-il200,000954.9 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1408-il200,000547.3 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1408-il500,000966.6 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1408-il500,000562.3 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca1408-il1,000,000972.7 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca1408-il1,000,000577.2 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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