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NACA 4418 (naca4418-il)

NACA 4418 - NACA 4418 airfoil


Airfoil naca4418-il
Details Dat file Parser  
(naca4418-il) NACA 4418
NACA 4418 airfoil
Max thickness 18% at 30% chord.
Max camber 4% at 40% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 4418
1.0000     0.0019
0.9500     0.0189
0.9000     0.0346
0.8000     0.0622
0.7000     0.0855
0.6000     0.1044
0.5000     0.1185
0.4000     0.1270
0.3000     0.1276
0.2500     0.1240
0.2000     0.1172
0.1500     0.1066
0.1000     0.0911
0.0750     0.0806
0.0500     0.0675
0.0250     0.0500
0.0125     0.0376
0.0000     0.0000
0.0125     -0.0211
0.0250     -0.0299
0.0500     -0.0406
0.0750     -0.0467
0.1000     -0.0506
0.1500     -0.0549
0.2000     -0.0556
0.2500     -0.0549
0.3000     -0.0526
0.4000     -0.0470
0.5000     -0.0402
0.6000     -0.0324
0.7000     -0.0245
0.8000     -0.0167
0.9000     -0.0093
0.9500     -0.0055
1.0000     -0.0019
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Selig format dat file

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Polars for NACA 4418 (naca4418-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca4418-il50,00095.3 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4418-il50,000523.1 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4418-il100,000943.3 at α=10°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4418-il100,000547.7 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4418-il200,000967 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4418-il200,000565.4 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4418-il500,000993.3 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4418-il500,000588 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca4418-il1,000,0009115.8 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca4418-il1,000,0005107.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
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