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S2050 8.93% (s2050-il)

S2050 8.93% - Selig S2050 low Reynolds number airfoil


Airfoil s2050-il
Details Dat file Parser  
(s2050-il) S2050 8.93%
Selig S2050 low Reynolds number airfoil
Max thickness 8.9% at 29.8% chord.
Max camber 1.1% at 69.5% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S2050 8.93%
       1.00000     0.00000  
       0.99673     0.00047  
       0.98732     0.00210  
       0.97251     0.00484  
       0.95280     0.00821  
       0.92826     0.01179  
       0.89894     0.01556  
       0.86520     0.01956  
       0.82744     0.02374  
       0.78613     0.02806  
       0.74177     0.03246  
       0.69492     0.03689  
       0.64622     0.04125  
       0.59626     0.04529  
       0.54553     0.04887  
       0.49454     0.05190  
       0.44383     0.05428  
       0.39393     0.05591  
       0.34531     0.05673  
       0.29847     0.05667  
       0.25386     0.05571  
       0.21189     0.05380  
       0.17293     0.05094  
       0.13731     0.04718  
       0.10534     0.04256  
       0.07728     0.03716  
       0.05332     0.03110  
       0.03363     0.02452  
       0.01833     0.01763  
       0.00756     0.01069  
       0.00137     0.00390  
       0.00034    -0.00192  
       0.00484    -0.00730  
       0.01443    -0.01287  
       0.02880    -0.01794  
       0.04792    -0.02231  
       0.07182    -0.02581  
       0.10040    -0.02854  
       0.13340    -0.03055  
       0.17052    -0.03189  
       0.21134    -0.03266  
       0.25539    -0.03289  
       0.30216    -0.03260  
       0.35111    -0.03183  
       0.40167    -0.03058  
       0.45327    -0.02884  
       0.50532    -0.02659  
       0.55720    -0.02379  
       0.60859    -0.02007  
       0.65946    -0.01567  
       0.70940    -0.01126  
       0.75762    -0.00722  
       0.80337    -0.00377  
       0.84590    -0.00106  
       0.88450     0.00084  
       0.91851     0.00190  
       0.94729     0.00216  
       0.97020     0.00173  
       0.98674     0.00098  
       0.99669     0.00030  
       1.00000     0.00000  
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Polars for S2050 8.93% (s2050-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s2050-il50,000933.2 at α=5.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s2050-il50,000534.6 at α=5.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s2050-il100,000948.8 at α=4.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s2050-il100,000547 at α=4.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s2050-il200,000963.5 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s2050-il200,000558.2 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s2050-il500,000980.9 at α=4.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s2050-il500,000570.6 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s2050-il1,000,000988.5 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s2050-il1,000,000580.8 at α=7°Mach=0 Ncrit=5Xfoil predictionDetails
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