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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(s4320-il) S4320 | Selig S4320 low Reynolds number airfoil Max thickness 9.4% at 26.8% chord Max camber 4.5% at 40.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s4320-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4320-il | 50,000 | 9 | 32.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4320-il | 50,000 | 5 | 40 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4320-il | 100,000 | 9 | 59.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4320-il | 100,000 | 5 | 61.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4320-il | 200,000 | 9 | 84.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4320-il | 200,000 | 5 | 82 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4320-il | 500,000 | 9 | 117.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4320-il | 500,000 | 5 | 106.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4320-il | 1,000,000 | 9 | 139.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4320-il | 1,000,000 | 5 | 122.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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