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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(s4310-il) S4310 | Selig S4310 low Reynolds number airfoil Max thickness 10.9% at 30.7% chord Max camber 4.2% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s4310-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4310-il | 50,000 | 9 | 28.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4310-il | 50,000 | 5 | 36.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4310-il | 100,000 | 9 | 56.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4310-il | 100,000 | 5 | 58.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4310-il | 200,000 | 9 | 81 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4310-il | 200,000 | 5 | 78.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4310-il | 500,000 | 9 | 112.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4310-il | 500,000 | 5 | 102.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4310-il | 1,000,000 | 9 | 134.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4310-il | 1,000,000 | 5 | 117.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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