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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(sd7037-il) SD7037-092-88 | Selig/Donovan SD7037 low Reynolds number airfoil Max thickness 9.2% at 26.1% chord Max camber 2.5% at 44.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd7037-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd7037-il | 50,000 | 9 | 34.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 50,000 | 5 | 39.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 100,000 | 9 | 55.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 100,000 | 5 | 55.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 200,000 | 9 | 74.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 200,000 | 5 | 70.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 500,000 | 9 | 99.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 500,000 | 5 | 90.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7037-il | 1,000,000 | 9 | 116 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7037-il | 1,000,000 | 5 | 104.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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