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NACA 66(3)-418 (naca663418-il)

NACA 66(3)-418 - NACA 66(3)-418 airfoil


Airfoil naca663418-il
Details Dat file Parser  
(naca663418-il) NACA 66(3)-418
NACA 66(3)-418 airfoil
Max thickness 18% at 44.9% chord.
Max camber 2.2% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 66(3)-418
1.00000     0.00000
0.95060     0.01275
0.90120     0.02744
0.85162     0.04276
0.80185     0.05794
0.75191     0.07238
0.70178     0.08539
0.65149     0.09639
0.60107     0.10464
0.55056     0.10923
0.50000     0.11148
0.44943     0.11188
0.39885     0.11059
0.34829     0.10759
0.29775     0.10287
0.24726     0.09633
0.19683     0.08773
0.14651     0.07669
0.09636     0.06231
0.07140     0.05347
0.04656     0.04306
0.02194     0.03000
0.00981     0.02147
0.00509     0.01692
0.00280     0.01405
0.00000     0.00000
0.00720     -0.01205
0.00991     -0.01412
0.01519     -0.01719
0.02806     -0.02256
0.05344     -0.03042
0.07860     -0.03651
0.10364     -0.04163
0.15349     -0.04977
0.20317     -0.05589
0.25274     -0.06053
0.30225     -0.06399
0.35171     -0.06639
0.40115     -0.06775
0.45057     -0.06808
0.50000     -0.06736
0.54944     -0.06543
0.59893     -0.06180
0.64851     -0.05519
0.69822     -0.04651
0.74809     -0.03658
0.79815     -0.02610
0.84838     -0.01584
0.89880     -0.00676
0.94940     -0.00011
1.00000     0.00000
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Polars for NACA 66(3)-418 (naca663418-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca663418-il50,000918.8 at α=12°Mach=0 Ncrit=9Xfoil predictionDetails
   naca663418-il50,000516.8 at α=10.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca663418-il100,000927 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca663418-il100,000525.1 at α=9.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca663418-il200,000942.7 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca663418-il200,000544.9 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca663418-il500,000991.5 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca663418-il500,000589.9 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca663418-il1,000,0009124 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca663418-il1,000,0005114.6 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
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