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S1210 12% (s1210-il)

S1210 12% - Selig S1210 high lift low Reynolds number airfoil


Airfoil s1210-il
Details Dat file Parser  
(s1210-il) S1210 12%
Selig S1210 high lift low Reynolds number airfoil
Max thickness 12% at 21.4% chord.
Max camber 6.7% at 51.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
       S1210 12% 
       1.00000     0.00000
       0.99837     0.00101
       0.99398     0.00397
       0.98753     0.00832
       0.97908     0.01317
       0.96811     0.01811
       0.95437     0.02328
       0.93796     0.02874
       0.91898     0.03443
       0.89754     0.04032
       0.87376     0.04637
       0.84779     0.05254
       0.81980     0.05879
       0.78997     0.06506
       0.75851     0.07130
       0.72561     0.07747
       0.69151     0.08349
       0.65642     0.08932
       0.62058     0.09490
       0.58423     0.10016
       0.54763     0.10505
       0.51105     0.10948
       0.47473     0.11335
       0.43891     0.11653
       0.40378     0.11892
       0.36955     0.12046
       0.33652     0.12091
       0.30456     0.12000
       0.27347     0.11784
       0.24341     0.11462
       0.21445     0.11047
       0.18681     0.10556
       0.16069     0.09994
       0.13622     0.09362
       0.11351     0.08672
       0.09269     0.07932
       0.07388     0.07149
       0.05719     0.06332
       0.04282     0.05484
       0.03068     0.04593
       0.02054     0.03672
       0.01239     0.02755
       0.00626     0.01866
       0.00217     0.01030
       0.00016     0.00277
       0.00023    -0.00345
       0.00337    -0.00773
       0.01034    -0.01070
       0.02071    -0.01324
       0.03417    -0.01529
       0.05052    -0.01685
       0.06959    -0.01786
       0.09118    -0.01830
       0.11512    -0.01810
       0.14119    -0.01715
       0.16911    -0.01524
       0.19906    -0.01183
       0.23157    -0.00697
       0.26670    -0.00124
       0.30427     0.00504
       0.34404     0.01158
       0.38575     0.01814
       0.42909     0.02446
       0.47370     0.03032
       0.51919     0.03551
       0.56515     0.03986
       0.61113     0.04320
       0.65666     0.04543
       0.70127     0.04646
       0.74446     0.04625
       0.78575     0.04479
       0.82465     0.04214
       0.86071     0.03837
       0.89349     0.03364
       0.92255     0.02809
       0.94754     0.02192
       0.96791     0.01530
       0.98299     0.00890
       0.99284     0.00390
       0.99828     0.00095
       1.00000     0.00000
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Polars for S1210 12% (s1210-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s1210-il50,000914.9 at α=2.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s1210-il50,000542.1 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s1210-il100,000959.3 at α=8°Mach=0 Ncrit=9Xfoil predictionDetails
   s1210-il100,000566 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s1210-il200,000986.3 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s1210-il200,000588 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s1210-il500,0009121.4 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s1210-il500,0005115 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s1210-il1,000,0009148 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s1210-il1,000,0005135.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
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