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NACA 2415 (naca2415-il)

NACA 2415 - NACA 2415 airfoil


Airfoil naca2415-il
Details Dat file Parser  
(naca2415-il) NACA 2415
NACA 2415 airfoil
Max thickness 15% at 30% chord.
Max camber 2% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 2415
1.0000     0.0016
0.9500     0.0134
0.9000     0.0245
0.8000     0.0441
0.7000     0.0610
0.6000     0.0750
0.5000     0.0857
0.4000     0.0925
0.3000     0.0938
0.2500     0.0917
0.2000     0.0870
0.1500     0.0797
0.1000     0.0683
0.0750     0.0606
0.0500     0.0507
0.0250     0.0371
0.0125     0.0271
0.0000     0.0000
0.0125     -0.0206
0.0250     -0.0286
0.0500     -0.0384
0.0750     -0.0447
0.1000     -0.0490
0.1500     -0.0542
0.2000     -0.0566
0.2500     -0.0570
0.3000     -0.0562
0.4000     -0.0525
0.5000     -0.0467
0.6000     -0.0390
0.7000     -0.0305
0.8000     -0.0215
0.9000     -0.0117
0.9500     -0.0068
1.0000     -0.0016
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Selig format dat file

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Polars for NACA 2415 (naca2415-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca2415-il50,000927.4 at α=9°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2415-il50,000531.4 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2415-il100,000946.7 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2415-il100,000547.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2415-il200,000964.1 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2415-il200,000561.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2415-il500,000986.3 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2415-il500,000579.5 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca2415-il1,000,0009102.2 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca2415-il1,000,000588.6 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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