Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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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 | Remove Airfoil details Airfoil plotter |
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Polars for (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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