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S1091 (s1091-il)

S1091 - Selig S1091 airfoil


Airfoil s1091-il
Details Dat file Parser  
(s1091-il) S1091
Selig S1091 airfoil
Max thickness 5.1% at 13.4% chord.
Max camber 5.7% at 45.1% chord
Source UIUC Airfoil Coordinates Database
Source dat file
The dat file is in Selig format
S1091
       1.00000     0.00000
       0.99821     0.00048
       0.99311     0.00197
       0.98508     0.00439
       0.97435     0.00751
       0.96107     0.01114
       0.94536     0.01510
       0.92724     0.01916
       0.90664     0.02323
       0.88358     0.02738
       0.85824     0.03164
       0.83079     0.03600
       0.80143     0.04041
       0.77035     0.04486
       0.73777     0.04930
       0.70392     0.05368
       0.66904     0.05794
       0.63336     0.06203
       0.59713     0.06588
       0.56060     0.06938
       0.52402     0.07244
       0.48752     0.07482
       0.45113     0.07648
       0.41500     0.07757
       0.37933     0.07808
       0.34435     0.07804
       0.31026     0.07745
       0.27726     0.07631
       0.24555     0.07460
       0.21527     0.07231
       0.18657     0.06943
       0.15955     0.06601
       0.13434     0.06210
       0.11106     0.05775
       0.08985     0.05302
       0.07079     0.04795
       0.05399     0.04260
       0.03955     0.03701
       0.02754     0.03123
       0.01797     0.02510
       0.01058     0.01865
       0.00513     0.01227
       0.00162     0.00629
       0.00005     0.00107
       0.00032    -0.00281
       0.00351    -0.00469
       0.01047    -0.00516
       0.02077    -0.00487
       0.03425    -0.00378
       0.05081    -0.00180
       0.07054     0.00115
       0.09361     0.00485
       0.11991     0.00918
       0.14930     0.01390
       0.18167     0.01886
       0.21682     0.02388
       0.25452     0.02879
       0.29452     0.03341
       0.33655     0.03759
       0.38032     0.04112
       0.42548     0.04385
       0.47168     0.04553
       0.51854     0.04594
       0.56545     0.04449
       0.61151     0.04098
       0.65477     0.03640
       0.69492     0.03184
       0.73321     0.02787
       0.76957     0.02424
       0.80388     0.02085
       0.83598     0.01770
       0.86570     0.01474
       0.89286     0.01197
       0.91729     0.00938
       0.93880     0.00698
       0.95720     0.00481
       0.97235     0.00299
       0.98421     0.00162
       0.99283     0.00072
       0.99817     0.00020
       1.00000     0.00000
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Polars for S1091 (s1091-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   s1091-il50,000946.1 at α=6.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s1091-il50,000548.3 at α=5.5°Mach=0 Ncrit=5Xfoil predictionDetails
   s1091-il100,000970.6 at α=5.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s1091-il100,000569.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s1091-il200,000996.2 at α=4°Mach=0 Ncrit=9Xfoil predictionDetails
   s1091-il200,000590.7 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   s1091-il500,0009129.8 at α=2.75°Mach=0 Ncrit=9Xfoil predictionDetails
   s1091-il500,0005111 at α=2.75°Mach=0 Ncrit=5Xfoil predictionDetails
   s1091-il1,000,0009153 at α=2.25°Mach=0 Ncrit=9Xfoil predictionDetails
   s1091-il1,000,0005117.7 at α=3.5°Mach=0 Ncrit=5Xfoil predictionDetails
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