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NACA 65(3)-218 (naca653218-il)

NACA 65(3)-218 - NACA 65(3)-218 airfoil


Airfoil naca653218-il
Details Dat file Parser  
(naca653218-il) NACA 65(3)-218
NACA 65(3)-218 airfoil
Max thickness 18% at 39.9% chord.
Max camber 1.1% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 65(3)-218
1.00000     0.00000
0.95023     0.00805
0.90046     0.01835
0.85063     0.02967
0.80074     0.04133
0.75077     0.05290
0.70073     0.06398
0.65065     0.07425
0.60047     0.08338
0.55026     0.09103
0.50000     0.09671
0.44972     0.09996
0.39942     0.10070
0.34912     0.09916
0.29884     0.09566
0.24858     0.09023
0.19835     0.08270
0.14818     0.07276
0.09809     0.05971
0.07311     0.05153
0.04819     0.04178
0.02340     0.02932
0.01110     0.02116
0.00625     0.01673
0.00388     0.01382
0.00000     0.00000
0.00612     -0.01282
0.00875     -0.01533
0.01390     -0.01902
0.02660     -0.02560
0.05181     -0.03546
0.07689     -0.04305
0.10191     -0.04937
0.15182     -0.05930
0.20165     -0.06676
0.25142     -0.07233
0.30116     -0.07622
0.35088     -0.07856
0.40058     -0.07928
0.45028     -0.07806
0.50000     -0.07465
0.54974     -0.06913
0.59953     -0.06196
0.64937     -0.05365
0.69927     -0.04454
0.74923     -0.03500
0.79926     -0.02541
0.84937     -0.01621
0.89954     -0.00801
0.94977     -0.00173
1.00000     0.00000
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Selig format dat file

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Polars for NACA 65(3)-218 (naca653218-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca653218-il50,000919.6 at α=11.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca653218-il50,000517.1 at α=9.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca653218-il100,000935.2 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca653218-il100,000531.9 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca653218-il200,000957.3 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca653218-il200,000556.7 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca653218-il500,000985.7 at α=6°Mach=0 Ncrit=9Xfoil predictionDetails
   naca653218-il500,000576.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca653218-il1,000,0009102.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca653218-il1,000,000586.1 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
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