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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(s2055-il) S2055 | Selig S2055 low Reynolds number airfoil Max thickness 8% at 34.8% chord Max camber 1.4% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(m17-il) NACA M17 AIRFOIL | NACA/Munk M-17 airfoil Max thickness 8.1% at 40% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s2055-il,m17-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s2055-il | 50,000 | 9 | 35.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 50,000 | 5 | 35.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 100,000 | 9 | 51.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 100,000 | 5 | 48.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 200,000 | 9 | 70.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 200,000 | 5 | 61.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 500,000 | 9 | 92.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 500,000 | 5 | 71.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s2055-il | 1,000,000 | 9 | 95.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s2055-il | 1,000,000 | 5 | 81 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 50,000 | 9 | 35.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 50,000 | 5 | 35.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 100,000 | 9 | 55.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 100,000 | 5 | 55.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 200,000 | 9 | 75.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 200,000 | 5 | 74.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 500,000 | 9 | 102.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 500,000 | 5 | 98.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m17-il | 1,000,000 | 9 | 122.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m17-il | 1,000,000 | 5 | 114.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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