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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(s4158-il) S4158 | Selig S4158 low Reynolds number airfoil Max thickness 10.9% at 35.3% chord Max camber 3.7% at 44.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s4158-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4158-il | 50,000 | 9 | 35.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4158-il | 50,000 | 5 | 32.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4158-il | 100,000 | 9 | 57.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4158-il | 100,000 | 5 | 55.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4158-il | 200,000 | 9 | 84.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4158-il | 200,000 | 5 | 80.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4158-il | 500,000 | 9 | 124.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4158-il | 500,000 | 5 | 109 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4158-il | 1,000,000 | 9 | 150.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4158-il | 1,000,000 | 5 | 124.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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