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NACA 64(3)-418 (naca643418-il)

NACA 64(3)-418 - NACA 64(3)-418 airfoil


Airfoil naca643418-il
Details Dat file Parser  
(naca643418-il) NACA 64(3)-418
NACA 64(3)-418 airfoil
Max thickness 17.9% at 34.8% chord.
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 64(3)-418
1.00000     0.00000
0.95037     0.01030
0.90077     0.02132
0.85108     0.03294
0.80127     0.04477
0.75135     0.05654
0.70131     0.06784
0.65114     0.07841
0.60086     0.08799
0.55047     0.09635
0.50000     0.10320
0.44945     0.10820
0.39885     0.11093
0.34823     0.11037
0.29763     0.10730
0.24707     0.10176
0.19657     0.09366
0.14617     0.08277
0.09595     0.06823
0.07095     0.05908
0.04609     0.04800
0.02152     0.03357
0.00950     0.02370
0.00486     0.01840
0.00263     0.01508
0.00000     0.00000
0.00737     -0.01308
0.01014     -0.01560
0.01550     -0.01942
0.02848     -0.02613
0.05391     -0.03536
0.07905     -0.04212
0.10405     -0.04755
0.15383     -0.05585
0.20343     -0.06182
0.25293     -0.06596
0.30237     -0.06842
0.35177     -0.06917
0.40115     -0.06809
0.45055     -0.06440
0.50000     -0.05908
0.54953     -0.05255
0.59914     -0.04515
0.64886     -0.03721
0.69869     -0.02896
0.74865     -0.02074
0.79873     -0.01293
0.84892     -0.00602
0.94963     0.00234
1.00000     0.00000
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Selig format dat file

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Polars for NACA 64(3)-418 (naca643418-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca643418-il50,000920.8 at α=11.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca643418-il50,000516.8 at α=11.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca643418-il100,000939.2 at α=9.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca643418-il100,000542.7 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca643418-il200,000969.3 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca643418-il200,000568.3 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca643418-il500,0009101.8 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca643418-il500,000593.5 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca643418-il1,000,0009123.7 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca643418-il1,000,0005109.2 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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