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Ornithopter airfoil. (s1020-il)

Ornithopter airfoil. - Selig S1020 ornithopter airfoil


Airfoil s1020-il
Details Dat file Parser  
(s1020-il) Ornithopter airfoil.
Selig S1020 ornithopter airfoil
Max thickness 15.1% at 33.8% chord.
Max camber 4.6% at 57% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
Ornithopter airfoil.
S1020
     1.00000   0.00000
     0.99637   0.00132
     0.98633   0.00544
     0.97138   0.01201
     0.95221   0.01987
     0.92858   0.02824
     0.90037   0.03716
     0.86802   0.04669
     0.83206   0.05668
     0.79303   0.06690
     0.75150   0.07709
     0.70800   0.08691
     0.66299   0.09599
     0.61686   0.10404
     0.57001   0.11082
     0.52281   0.11615
     0.47565   0.11991
     0.42893   0.12200
     0.38308   0.12232
     0.33841   0.12081
     0.29521   0.11747
     0.25379   0.11243
     0.21447   0.10583
     0.17759   0.09786
     0.14348   0.08869
     0.11246   0.07850
     0.08479   0.06752
     0.06069   0.05597
     0.04036   0.04414
     0.02399   0.03235
     0.01172   0.02092
     0.00368   0.01030
     0.00006   0.00111
     0.00210  -0.00597
     0.01048  -0.01176
     0.02453  -0.01716
     0.04387  -0.02193
     0.06822  -0.02596
     0.09729  -0.02919
     0.13077  -0.03158
     0.16828  -0.03309
     0.20943  -0.03370
     0.25378  -0.03334
     0.30086  -0.03199
     0.35023  -0.02957
     0.40159  -0.02597
     0.45480  -0.02141
     0.50939  -0.01639
     0.56466  -0.01126
     0.61990  -0.00630
     0.67438  -0.00178
     0.72731   0.00203
     0.77785   0.00495
     0.82515   0.00682
     0.86836   0.00760
     0.90663   0.00733
     0.93918   0.00618
     0.96531   0.00441
     0.98443   0.00242
     0.99609   0.00071
     1.00000   0.00000
Dat file parser warnings
  • Line 2 - Invalid characters : S1020
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Polars for Ornithopter airfoil. (s1020-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s1020-il50,00096 at α=8.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s1020-il50,000518.1 at α=8.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s1020-il100,000949.8 at α=10.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s1020-il100,000553.4 at α=7.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s1020-il200,000982.4 at α=7.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s1020-il200,000581.5 at α=5.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s1020-il500,0009120 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   s1020-il500,0005111.2 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s1020-il1,000,0009146.8 at α=5°Mach=0 Ncrit=9Xfoil predictionDetails
   s1020-il1,000,0005127.2 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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