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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(sd6060-il) SD6060-104-88 | Selig/Donovan SD6060 low Reynolds number airfoil Max thickness 10.4% at 33.9% chord Max camber 1.6% at 38.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd6060-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd6060-il | 50,000 | 9 | 33.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd6060-il | 50,000 | 5 | 34.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd6060-il | 100,000 | 9 | 51.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd6060-il | 100,000 | 5 | 50.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd6060-il | 200,000 | 9 | 70.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd6060-il | 200,000 | 5 | 65.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd6060-il | 500,000 | 9 | 94.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd6060-il | 500,000 | 5 | 80.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd6060-il | 1,000,000 | 9 | 105.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd6060-il | 1,000,000 | 5 | 87 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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