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NACA 63(3)-018 (naca633018-il)

NACA 63(3)-018 - NACA 63(3)-018 airfoil


Airfoil naca633018-il
Details Dat file Parser  
(naca633018-il) NACA 63(3)-018
NACA 63(3)-018 airfoil
Max thickness 18% at 33.9% chord.
Max camber 0% at 0% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 63(3)-018
1.00000     0.00000
0.99893     0.00006
0.99572     0.00024
0.99039     0.00053
0.98296     0.00096
0.97347     0.00157
0.96194     0.00244
0.94844     0.00368
0.93301     0.00539
0.91573     0.00761
0.89668     0.01035
0.87592     0.01359
0.85355     0.01730
0.82967     0.02149
0.80438     0.02613
0.77779     0.03117
0.75000     0.03655
0.72114     0.04216
0.69134     0.04793
0.66072     0.05373
0.62941     0.05947
0.59755     0.06502
0.56526     0.07029
0.53270     0.07515
0.50000     0.07949
0.46730     0.08321
0.43474     0.08620
0.40245     0.08839
0.37059     0.08969
0.33928     0.09007
0.30866     0.08955
0.27886     0.08820
0.25000     0.08611
0.22221     0.08336
0.19562     0.07999
0.17033     0.07607
0.14645     0.07168
0.12408     0.06688
0.10332     0.06171
0.08427     0.05620
0.06699     0.05041
0.05156     0.04442
0.03806     0.03833
0.02653     0.03214
0.01704     0.02561
0.00961     0.01861
0.00428     0.01164
0.00107     0.00539
0.00000     0.00000
0.00107     -0.00539
0.00428     -0.01164
0.00961     -0.01861
0.01704     -0.02561
0.02653     -0.03214
0.03806     -0.03833
0.05156     -0.04442
0.06699     -0.05041
0.08427     -0.05620
0.10332     -0.06171
0.12408     -0.06688
0.14645     -0.07168
0.17033     -0.07607
0.19562     -0.07999
0.22221     -0.08336
0.25000     -0.08611
0.27886     -0.08820
0.30866     -0.08955
0.33928     -0.09007
0.37059     -0.08969
0.40245     -0.08839
0.43474     -0.08620
0.46730     -0.08321
0.50000     -0.07949
0.53270     -0.07515
0.56526     -0.07029
0.59755     -0.06502
0.62941     -0.05947
0.66072     -0.05373
0.69134     -0.04793
0.72114     -0.04216
0.75000     -0.03655
0.77779     -0.03117
0.80438     -0.02613
0.82967     -0.02149
0.85355     -0.01730
0.87592     -0.01359
0.89668     -0.01035
0.91573     -0.00761
0.93301     -0.00539
0.94844     -0.00368
0.96194     -0.00244
0.97347     -0.00157
0.98296     -0.00096
0.99039     -0.00053
0.99572     -0.00024
0.99893     -0.00006
1.00000     0.00000
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Selig format dat file

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Polars for NACA 63(3)-018 (naca633018-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca633018-il50,000923.4 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633018-il50,000520.6 at α=8°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633018-il100,000940.7 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633018-il100,000536.4 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633018-il200,000953.3 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633018-il200,000550.2 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633018-il500,000973 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633018-il500,000561.4 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca633018-il1,000,000983 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca633018-il1,000,000565.4 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
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