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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(sd2083-il) SD2083 (9.0%) | Selig/Donovan SD2083 low Reynolds number airfoil Max thickness 9% at 35.2% chord Max camber 2.5% at 49.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd2083-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd2083-il | 50,000 | 9 | 37.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd2083-il | 50,000 | 5 | 38.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd2083-il | 100,000 | 9 | 58.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd2083-il | 100,000 | 5 | 56.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd2083-il | 200,000 | 9 | 80.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd2083-il | 200,000 | 5 | 74 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd2083-il | 500,000 | 9 | 109 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd2083-il | 500,000 | 5 | 93.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd2083-il | 1,000,000 | 9 | 127.3 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd2083-il | 1,000,000 | 5 | 102.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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