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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(sd2030-il) SD2030-086-88 | Selig/Donovan SD2030 low Reynolds number airfoil Max thickness 8.6% at 35.5% chord Max camber 2.2% at 45.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd2030-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd2030-il | 50,000 | 9 | 37.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd2030-il | 50,000 | 5 | 37.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd2030-il | 100,000 | 9 | 56.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd2030-il | 100,000 | 5 | 52.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd2030-il | 200,000 | 9 | 77.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd2030-il | 200,000 | 5 | 68.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd2030-il | 500,000 | 9 | 104.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd2030-il | 500,000 | 5 | 81 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd2030-il | 1,000,000 | 9 | 112.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd2030-il | 1,000,000 | 5 | 87.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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