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NACA 63(2)-615 (naca632615-il)

NACA 63(2)-615 - NACA 63(2)-615 airfoil


Airfoil naca632615-il
Details Dat file Parser  
(naca632615-il) NACA 63(2)-615
NACA 63(2)-615 airfoil
Max thickness 15% at 34.8% chord.
Max camber 3.3% at 50% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 63(2)-615
1.00000     0.00000
0.95042     0.01245
0.90089     0.02398
0.85127     0.03555
0.80153     0.04693
0.75163     0.05800
0.70159     0.06847
0.65139     0.07809
0.60105     0.08665
0.55058     0.09393
0.50000     0.09974
0.44932     0.10384
0.39857     0.10598
0.34778     0.10587
0.29700     0.10331
0.24625     0.09830
0.19558     0.09066
0.14504     0.08010
0.09473     0.06578
0.06973     0.05667
0.04492     0.04560
0.02050     0.03129
0.00866     0.02159
0.00418     0.01634
0.00205     0.01317
0.00000     0.00000
0.00795     -0.01017
0.01082     -0.01214
0.01634     -0.01517
0.02950     -0.02013
0.05508     -0.02664
0.08027     -0.03123
0.10527     -0.03476
0.15496     -0.03972
0.20442     -0.04290
0.25375     -0.04460
0.30300     -0.04499
0.35222     -0.04407
0.40143     -0.04172
0.45068     -0.03814
0.50000     -0.03356
0.54942     -0.02823
0.59895     -0.02239
0.64861     -0.01629
0.69841     -0.01015
0.74837     -0.00430
0.79847     0.00083
0.84873     0.00483
0.89911     0.00704
0.94958     0.00651
1.00000     0.00000
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Selig format dat file

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Polars for NACA 63(2)-615 (naca632615-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca632615-il50,000927.8 at α=10.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca632615-il50,000524.9 at α=9.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca632615-il100,000955 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca632615-il100,000555.6 at α=7.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca632615-il200,000981.7 at α=7.5°Mach=0 Ncrit=9Xfoil predictionDetails
   naca632615-il200,000578.1 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca632615-il500,0009112.2 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca632615-il500,0005104.5 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca632615-il1,000,0009134.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca632615-il1,000,0005121.6 at α=4°Mach=0 Ncrit=5Xfoil predictionDetails
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