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NACA 63(2)A-015 (naca632a015-il)

NACA 63(2)A-015 - NACA 63(2)A-015 airfoil


Airfoil naca632a015-il
Details Dat file Parser  
(naca632a015-il) NACA 63(2)A-015
NACA 63(2)A-015 airfoil
Max thickness 15% at 37.1% chord.
Max camber 1.7% at 14.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
NACA 63(2)A-015
1.00000     0.00000
0.99893     0.00020
0.99572     0.00079
0.99039     0.00176
0.98296     0.00311
0.97347     0.00482
0.96194     0.00686
0.94844     0.00919
0.93301     0.01179
0.91573     0.01466
0.89668     0.01785
0.87592     0.02137
0.85355     0.02518
0.82967     0.02921
0.80438     0.03343
0.77779     0.03786
0.75000     0.04253
0.72114     0.04744
0.69134     0.05245
0.66072     0.05740
0.62941     0.06223
0.59755     0.06691
0.56526     0.07134
0.53270     0.07535
0.50000     0.07891
0.46730     0.08204
0.43474     0.08461
0.40245     0.08652
0.37059     0.08776
0.33928     0.08827
0.30866     0.08808
0.27886     0.08732
0.25000     0.08603
0.22221     0.08421
0.19562     0.08191
0.17033     0.07914
0.14645     0.07580
0.12408     0.07177
0.10332     0.06698
0.08427     0.06150
0.06699     0.05559
0.05156     0.04920
0.03806     0.04250
0.02653     0.03580
0.01704     0.02870
0.00961     0.02175
0.00428     0.01450
0.00107     0.00730
0.00000     0.00000
0.00107     -0.00460
0.00428     -0.00860
0.00961     -0.01224
0.01704     -0.01591
0.02653     -0.01902
0.03806     -0.02196
0.05156     -0.02493
0.06699     -0.02800
0.08427     -0.03116
0.10332     -0.03449
0.12408     -0.03808
0.14645     -0.04191
0.17033     -0.04583
0.19562     -0.04956
0.22221     -0.05288
0.25000     -0.05577
0.27886     -0.05827
0.30866     -0.06020
0.33928     -0.06146
0.37059     -0.06211
0.40245     -0.06211
0.43474     -0.06142
0.46730     -0.06013
0.50000     -0.05828
0.53270     -0.05590
0.56526     -0.05318
0.59755     -0.05016
0.62941     -0.04678
0.66072     -0.04314
0.69134     -0.03939
0.72114     -0.03564
0.75000     -0.03195
0.77779     -0.02841
0.80438     -0.02503
0.82967     -0.02182
0.85355     -0.01878
0.87592     -0.01594
0.89668     -0.01330
0.91573     -0.01087
0.93301     -0.00867
0.94844     -0.00671
0.96194     -0.00498
0.97347     -0.00349
0.98296     -0.00225
0.99039     -0.00127
0.99572     -0.00057
0.99893     -0.00014
1.00000     0.00000
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Polars for NACA 63(2)A-015 (naca632a015-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   naca632a015-il50,000923.3 at α=7.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca632a015-il50,000529.7 at α=6.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca632a015-il100,000945.8 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca632a015-il100,000545.1 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   naca632a015-il200,000959.7 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   naca632a015-il200,000555.6 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   naca632a015-il500,000976.7 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   naca632a015-il500,000572.9 at α=8.5°Mach=0 Ncrit=5Xfoil predictionDetails
   naca632a015-il1,000,000993.1 at α=8.75°Mach=0 Ncrit=9Xfoil predictionDetails
   naca632a015-il1,000,000584.9 at α=8.25°Mach=0 Ncrit=5Xfoil predictionDetails
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