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S6061 9% (s6061-il)

S6061 9% - Selig S6061 low Reynolds number airfoil


Airfoil s6061-il
Details Dat file Parser  
(s6061-il) S6061 9%
Selig S6061 low Reynolds number airfoil
Max thickness 9% at 34% chord.
Max camber 1.5% at 43.6% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
 S6061 9%
     1.00000   0.00000
     0.99674   0.00022
     0.98707   0.00100
     0.97131   0.00255
     0.94987   0.00497
     0.92321   0.00829
     0.89186   0.01244
     0.85637   0.01728
     0.81726   0.02264
     0.77507   0.02832
     0.73032   0.03410
     0.68352   0.03977
     0.63517   0.04512
     0.58576   0.05001
     0.53580   0.05427
     0.48580   0.05776
     0.43623   0.06032
     0.38750   0.06185
     0.34000   0.06231
     0.29417   0.06175
     0.25047   0.06018
     0.20931   0.05761
     0.17107   0.05408
     0.13608   0.04961
     0.10463   0.04431
     0.07697   0.03826
     0.05331   0.03161
     0.03379   0.02455
     0.01856   0.01732
     0.00771   0.01020
     0.00135   0.00364
     0.00030  -0.00161
     0.00507  -0.00618
     0.01525  -0.01080
     0.03050  -0.01506
     0.05071  -0.01880
     0.07572  -0.02193
     0.10534  -0.02443
     0.13931  -0.02629
     0.17729  -0.02754
     0.21892  -0.02821
     0.26374  -0.02836
     0.31128  -0.02804
     0.36098  -0.02729
     0.41230  -0.02615
     0.46466  -0.02466
     0.51746  -0.02284
     0.57012  -0.02070
     0.62210  -0.01826
     0.67288  -0.01560
     0.72194  -0.01280
     0.76876  -0.01002
     0.81279  -0.00739
     0.85345  -0.00507
     0.89016  -0.00317
     0.92237  -0.00173
     0.94954  -0.00076
     0.97124  -0.00020
     0.98708   0.00002
     0.99674   0.00003
     1.00000   0.00000
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Lednicer format dat file
Selig format dat file

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Polars for S6061 9% (s6061-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s6061-il50,000934.1 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s6061-il50,000535.9 at α=6°Mach=0 Ncrit=5Xfoil predictionDetails
   s6061-il100,000951.2 at α=5.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s6061-il100,000550.1 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s6061-il200,000968.2 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   s6061-il200,000563.3 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s6061-il500,000988.8 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   s6061-il500,000577.3 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s6061-il1,000,0009102 at α=3.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s6061-il1,000,000581.7 at α=3.75°Mach=0 Ncrit=5Xfoil predictionDetails
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