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S5020 (s5020-il)

S5020 - Selig S5020 low Reynolds number airfoil


Airfoil s5020-il
Details Dat file Parser  
(s5020-il) S5020
Selig S5020 low Reynolds number airfoil
Max thickness 8.4% at 27.8% chord.
Max camber 2.2% at 27.8% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S5020
         1.0000000      0.0000000
         0.9968300     -0.0000100
         0.9873600      0.0000000
         0.9716000      0.0001500
         0.9496400      0.0006600
         0.9217100      0.0018600
         0.8883300      0.0041300
         0.8502600      0.0076600
         0.8084000      0.0123400
         0.7633900      0.0179500
         0.7159400      0.0243000
         0.6667200      0.0311600
         0.6164400      0.0382700
         0.5657600      0.0452400
         0.5151900      0.0517000
         0.4651600      0.0573600
         0.4160800      0.0619800
         0.3683000      0.0653900
         0.3221800      0.0674800
         0.2780300      0.0682100
         0.2362000      0.0675900
         0.1970200      0.0656500
         0.1608100      0.0624400
         0.1278500      0.0580200
         0.0983700      0.0524900
         0.0725700      0.0459600
         0.0505900      0.0386200
         0.0325200      0.0306500
         0.0184300      0.0223400
         0.0083300      0.0140100
         0.0021900      0.0061300
         0.0000200     -0.0004900
         0.0030800     -0.0050700
         0.0122600     -0.0081500
         0.0272700     -0.0103700
         0.0480700     -0.0119200
         0.0743400     -0.0131000
         0.1056300     -0.0140400
         0.1414800     -0.0147800
         0.1814100     -0.0153400
         0.2249100     -0.0156900
         0.2715000     -0.0158300
         0.3206400     -0.0157600
         0.3717900     -0.0155000
         0.4243600     -0.0150700
         0.4777600     -0.0144900
         0.5313900     -0.0137900
         0.5846200     -0.0129700
         0.6368700     -0.0120600
         0.6875200     -0.0110800
         0.7360100     -0.0100400
         0.7817800     -0.0089600
         0.8243000     -0.0078500
         0.8630800     -0.0067200
         0.8976700     -0.0055700
         0.9276700     -0.0044000
         0.9527600     -0.0031700
         0.9727900     -0.0018800
         0.9876300     -0.0007900
         0.9968600     -0.0001600
         1.0000000      0.0000000
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Polars for S5020 (s5020-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s5020-il50,000925.3 at α=8.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s5020-il50,000533.8 at α=7.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s5020-il100,000946 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s5020-il100,000548.9 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s5020-il200,000964.4 at α=6.5°Mach=0 Ncrit=9Xfoil predictionDetails
   s5020-il200,000563.6 at α=6.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s5020-il500,000988 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s5020-il500,000582.5 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s5020-il1,000,0009104.4 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s5020-il1,000,000596.7 at α=6.25°Mach=0 Ncrit=5Xfoil predictionDetails
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