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NACA 66(2)-415 (naca662415-il)

NACA 66(2)-415 - NACA 66(2)-415 airfoil


Airfoil naca662415-il
Details Dat file Parser  
(naca662415-il) NACA 66(2)-415
NACA 66(2)-415 airfoil
Max thickness 15% at 45% 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(2)-415
1.00000     0.00000
0.95053     0.01196
0.90104     0.02519
0.85139     0.03872
0.80159     0.05187
0.75162     0.06419
0.70150     0.07518
0.65126     0.08431
0.60090     0.09100
0.55046     0.09473
0.50000     0.09656
0.44952     0.09685
0.39904     0.09571
0.34857     0.09309
0.29812     0.08897
0.24771     0.08329
0.19736     0.07581
0.14709     0.06624
0.09696     0.05381
0.07199     0.04617
0.04711     0.03718
0.02241     0.02592
0.01019     0.01873
0.00544     0.01467
0.00314     0.01206
0.00000     0.00000
0.00686     -0.01006
0.00956     -0.01187
0.01481     -0.01445
0.02759     -0.01848
0.05289     -0.02454
0.07801     -0.02921
0.10304     -0.03313
0.15291     -0.03932
0.20264     -0.04397
0.25229     -0.04749
0.30188     -0.05009
0.35143     -0.05189
0.40096     -0.05287
0.45048     -0.05305
0.50000     -0.05244
0.54954     -0.05093
0.59910     -0.04816
0.64874     -0.04311
0.69850     -0.03630
0.74838     -0.02839
0.79841     -0.02003
0.84861     -0.01180
0.89896     -0.00451
0.94947     0.00068
1.00000     0.00000
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Lednicer format dat file
Selig format dat file

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Polars for NACA 66(2)-415 (naca662415-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca662415-il50,000921.9 at α=9.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca662415-il50,000521.4 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca662415-il100,000933.5 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca662415-il100,000532.7 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
   naca662415-il200,000955.4 at α=6.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca662415-il200,000555.3 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca662415-il500,000994 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca662415-il500,000589.2 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   naca662415-il1,000,0009120.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   naca662415-il1,000,0005107.6 at α=3°Mach=0 Ncrit=5Xfoil predictionDetails
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