S1012 (s1012-il)
S1012 - Selig S1012 HPV airfoil
| Details | Dat file | Parser | |
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(s1012-il) S1012 Selig S1012 HPV airfoil Max thickness 12% at 37.3% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S1012
1.00000 0.00000
0.99640 0.00018
0.98580 0.00094
0.96872 0.00264
0.94571 0.00536
0.91728 0.00912
0.88401 0.01398
0.84664 0.01993
0.80601 0.02677
0.76300 0.03416
0.71846 0.04139
0.67266 0.04740
0.62512 0.05182
0.57587 0.05510
0.52548 0.05748
0.47451 0.05907
0.42356 0.05994
0.37324 0.06011
0.32414 0.05961
0.27682 0.05846
0.23184 0.05667
0.18974 0.05425
0.15105 0.05120
0.11622 0.04747
0.08566 0.04299
0.05966 0.03766
0.03835 0.03142
0.02177 0.02428
0.00984 0.01640
0.00251 0.00810
0.00000 0.00000
0.00251 -0.00810
0.00984 -0.01640
0.02177 -0.02428
0.03835 -0.03142
0.05966 -0.03766
0.08566 -0.04299
0.11622 -0.04747
0.15105 -0.05120
0.18974 -0.05425
0.23184 -0.05667
0.27682 -0.05846
0.32414 -0.05961
0.37324 -0.06011
0.42356 -0.05994
0.47451 -0.05907
0.52548 -0.05748
0.57587 -0.05510
0.62512 -0.05182
0.67266 -0.04740
0.71846 -0.04139
0.76300 -0.03416
0.80601 -0.02677
0.84664 -0.01993
0.88401 -0.01398
0.91728 -0.00912
0.94571 -0.00536
0.96872 -0.00264
0.98580 -0.00094
0.99640 -0.00018
1.00000 0.00000
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Polars for S1012 (s1012-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1012-il | 50,000 | 9 | 26.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 50,000 | 5 | 25.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 100,000 | 9 | 37.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 100,000 | 5 | 31.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 200,000 | 9 | 37.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 200,000 | 5 | 40 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 500,000 | 9 | 53.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 500,000 | 5 | 56.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1012-il | 1,000,000 | 9 | 69.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1012-il | 1,000,000 | 5 | 70.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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