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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(s8055-il) S8055 (12%) | Selig S8055 (12%) low Reynolds number airfoil Max thickness 12% at 33.9% chord Max camber 1.6% at 44.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s8055-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s8055-il | 50,000 | 9 | 32.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 50,000 | 5 | 32.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 100,000 | 9 | 50.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 100,000 | 5 | 48.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 200,000 | 9 | 71 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 200,000 | 5 | 62.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 500,000 | 9 | 86.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 500,000 | 5 | 74.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s8055-il | 1,000,000 | 9 | 95 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s8055-il | 1,000,000 | 5 | 88.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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