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S6062 8% (s6062-il)

S6062 8% - Selig S6062 low Reynolds number airfoil


Airfoil s6062-il
Details Dat file Parser  
(s6062-il) S6062 8%
Selig S6062 low Reynolds number airfoil
Max thickness 7.9% at 29.4% chord.
Max camber 1.4% at 43.7% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
  S6062 8%
     1.00000   0.00000
     0.99680   0.00020
     0.98733   0.00088
     0.97184   0.00225
     0.95072   0.00438
     0.92441   0.00730
     0.89341   0.01095
     0.85821   0.01522
     0.81934   0.01994
     0.77733   0.02496
     0.73267   0.03005
     0.68588   0.03506
     0.63746   0.03978
     0.58788   0.04408
     0.53767   0.04783
     0.48734   0.05093
     0.43737   0.05323
     0.38823   0.05467
     0.34037   0.05520
     0.29424   0.05479
     0.25026   0.05344
     0.20882   0.05117
     0.17033   0.04804
     0.13513   0.04409
     0.10353   0.03938
     0.07580   0.03401
     0.05216   0.02810
     0.03276   0.02178
     0.01774   0.01528
     0.00715   0.00884
     0.00107   0.00295
     0.00045  -0.00181
     0.00563  -0.00607
     0.01601  -0.01033
     0.03144  -0.01419
     0.05180  -0.01752
     0.07696  -0.02024
     0.10672  -0.02234
     0.14083  -0.02382
     0.17897  -0.02471
     0.22075  -0.02507
     0.26575  -0.02494
     0.31346  -0.02440
     0.36335  -0.02349
     0.41486  -0.02225
     0.46742  -0.02074
     0.52041  -0.01900
     0.57326  -0.01706
     0.62537  -0.01496
     0.67617  -0.01273
     0.72513  -0.01044
     0.77171  -0.00816
     0.81540  -0.00600
     0.85566  -0.00409
     0.89194  -0.00252
     0.92370  -0.00135
     0.95045  -0.00056
     0.97178  -0.00012
     0.98733   0.00004
     0.99681   0.00003
     1.00000   0.00000
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Lednicer format dat file
Selig format dat file

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Polars for S6062 8% (s6062-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s6062-il50,000934.6 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s6062-il50,000535.6 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s6062-il100,000950.4 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s6062-il100,000548.4 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s6062-il200,000965.2 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s6062-il200,000558.8 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s6062-il500,000982 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s6062-il500,000568.4 at α=2.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s6062-il1,000,000991 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s6062-il1,000,000573.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
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