S1010 HPV airfoil (s1010-il)
S1010 HPV airfoil - Selig S1010 HPV airfoil
| Details | Dat file | Parser | |
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(s1010-il) S1010 HPV airfoil Selig S1010 HPV airfoil Max thickness 6% at 23.3% chord. Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
S1010 HPV airfoil
1.00000 0.00000
0.99681 0.00011
0.98742 0.00058
0.97219 0.00153
0.95153 0.00292
0.92572 0.00466
0.89507 0.00673
0.86004 0.00916
0.82114 0.01188
0.77893 0.01477
0.73398 0.01763
0.68672 0.02014
0.63738 0.02220
0.58637 0.02394
0.53426 0.02546
0.48168 0.02678
0.42926 0.02790
0.37759 0.02883
0.32731 0.02952
0.27899 0.02996
0.23322 0.03011
0.19053 0.02992
0.15147 0.02931
0.11647 0.02816
0.08589 0.02633
0.05996 0.02363
0.03869 0.02003
0.02209 0.01557
0.01007 0.01044
0.00259 0.00500
0.00000 0.00000
0.00259 -0.00500
0.01007 -0.01044
0.02209 -0.01557
0.03869 -0.02003
0.05996 -0.02363
0.08589 -0.02633
0.11647 -0.02816
0.15147 -0.02931
0.19053 -0.02992
0.23322 -0.03011
0.27899 -0.02996
0.32731 -0.02952
0.37759 -0.02883
0.42926 -0.02790
0.48168 -0.02678
0.53426 -0.02546
0.58637 -0.02394
0.63738 -0.02220
0.68672 -0.02014
0.73398 -0.01763
0.77893 -0.01477
0.82114 -0.01188
0.86004 -0.00916
0.89507 -0.00673
0.92572 -0.00466
0.95153 -0.00292
0.97219 -0.00153
0.98742 -0.00058
0.99681 -0.00011
1.00000 0.00000
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Polars for S1010 HPV airfoil (s1010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s1010-il | 50,000 | 9 | 20.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1010-il | 50,000 | 5 | 21.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1010-il | 100,000 | 9 | 29.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1010-il | 100,000 | 5 | 29.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1010-il | 200,000 | 9 | 37.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1010-il | 200,000 | 5 | 40.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1010-il | 500,000 | 9 | 53.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1010-il | 500,000 | 5 | 55.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1010-il | 1,000,000 | 9 | 66.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1010-il | 1,000,000 | 5 | 69.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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