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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(s8037-il) S8037 (16%) | Selig S8037 low Reynolds number airfoil Max thickness 16% at 33.5% chord Max camber 1.9% at 40.4% chord | Remove Airfoil details Airfoil plotter |
(s5020-il) S5020 | Selig S5020 low Reynolds number airfoil Max thickness 8.4% at 27.8% chord Max camber 2.2% at 27.8% chord | Remove Airfoil details Airfoil plotter |
(s4180-il) S4180-098-84 | Selig S4180 low Reynolds number airfoil Max thickness 9.8% at 26.1% chord Max camber 4% at 39.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s8037-il,s5020-il,s4180-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s8037-il | 50,000 | 9 | 7.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8037-il | 50,000 | 5 | 22.8 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8037-il | 100,000 | 9 | 47 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8037-il | 100,000 | 5 | 48.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8037-il | 200,000 | 9 | 71.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8037-il | 200,000 | 5 | 69 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8037-il | 500,000 | 9 | 99.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8037-il | 500,000 | 5 | 85.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8037-il | 1,000,000 | 9 | 110.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8037-il | 1,000,000 | 5 | 98.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 50,000 | 9 | 25.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 50,000 | 5 | 33.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 100,000 | 9 | 46 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 100,000 | 5 | 48.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 200,000 | 9 | 64.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 200,000 | 5 | 63.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 500,000 | 9 | 88 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 500,000 | 5 | 82.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s5020-il | 1,000,000 | 9 | 104.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s5020-il | 1,000,000 | 5 | 96.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 50,000 | 9 | 28.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 50,000 | 5 | 37.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 100,000 | 9 | 55.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 100,000 | 5 | 58.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 200,000 | 9 | 78.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 200,000 | 5 | 78.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 500,000 | 9 | 110.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 500,000 | 5 | 104.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4180-il | 1,000,000 | 9 | 133.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4180-il | 1,000,000 | 5 | 122.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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