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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(sd7062-il) SD7062 (14%) | Selig/Donovan SD7062 low Reynolds number airfoil Max thickness 14% at 25.5% chord Max camber 3.5% at 38.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd7062-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd7062-il | 50,000 | 9 | 12.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7062-il | 50,000 | 5 | 32.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7062-il | 100,000 | 9 | 47.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7062-il | 100,000 | 5 | 52.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7062-il | 200,000 | 9 | 70 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7062-il | 200,000 | 5 | 70.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7062-il | 500,000 | 9 | 99.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7062-il | 500,000 | 5 | 94.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7062-il | 1,000,000 | 9 | 121.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7062-il | 1,000,000 | 5 | 113.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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