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NACA 66(3)-218 (naca663218-il)

NACA 66(3)-218 - NACA 66(3)-218 airfoil


Airfoil naca663218-il
Details Dat file Parser  
(naca663218-il) NACA 66(3)-218
NACA 66(3)-218 airfoil
Max thickness 18% at 45% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 66(3)-218
1.00000     0.00000
0.95030     0.00961
0.90060     0.02230
0.85081     0.03606
0.80093     0.05001
0.75095     0.06345
0.70089     0.07568
0.65075     0.08610
0.60054     0.09394
0.55028     0.09828
0.50000     0.10045
0.44971     0.10093
0.39942     0.09989
0.34914     0.09731
0.29887     0.09317
0.24863     0.08742
0.19841     0.07982
0.14825     0.07004
0.09818     0.05724
0.07320     0.04933
0.04827     0.04002
0.02346     0.02828
0.01115     0.02054
0.00628     0.01636
0.00389     0.01368
0.00000     0.00000
0.00611     -0.01268
0.00872     -0.01496
0.01385     -0.01840
0.02654     -0.02456
0.05173     -0.03370
0.07680     -0.04085
0.10182     -0.04690
0.15175     -0.05658
0.20159     -0.06390
0.25137     -0.06952
0.30113     -0.07373
0.35086     -0.07671
0.40058     -0.07847
0.45029     -0.07903
0.50000     -0.07839
0.54972     -0.07638
0.59946     -0.07252
0.64925     -0.06550
0.69911     -0.05624
0.74905     -0.04555
0.79907     -0.03409
0.84919     -0.02260
0.89940     -0.01196
0.94970     -0.00329
1.00000     0.00000
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Selig format dat file

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Polars for NACA 66(3)-218 (naca663218-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca663218-il50,000919.3 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca663218-il50,000516.9 at α=9°Mach=0 Ncrit=5Xfoil predictionDetails
   naca663218-il100,000926.7 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   naca663218-il100,000522.9 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca663218-il200,000938.4 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca663218-il200,000541.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca663218-il500,000976.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca663218-il500,000572.3 at α=4.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca663218-il1,000,000999.1 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca663218-il1,000,000587.2 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
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