S1091 (s1091-il)
S1091 - Selig S1091 airfoil
| Details | Dat file | Parser | |
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(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)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1091-il | 50,000 | 9 | 46.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 50,000 | 5 | 48.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 100,000 | 9 | 70.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 100,000 | 5 | 69.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 200,000 | 9 | 96.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 200,000 | 5 | 90.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 500,000 | 9 | 129.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 500,000 | 5 | 111 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1091-il | 1,000,000 | 9 | 153 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1091-il | 1,000,000 | 5 | 117.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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