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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(sd7034-il) SD7034 | Selig/Donovan SD7034 low Reynolds number airfoil Max thickness 10.5% at 26% chord Max camber 3.6% at 39.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd7034-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd7034-il | 50,000 | 9 | 27.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7034-il | 50,000 | 5 | 37.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7034-il | 100,000 | 9 | 54.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7034-il | 100,000 | 5 | 57.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7034-il | 200,000 | 9 | 77.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7034-il | 200,000 | 5 | 76.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7034-il | 500,000 | 9 | 107.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7034-il | 500,000 | 5 | 99.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7034-il | 1,000,000 | 9 | 128.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7034-il | 1,000,000 | 5 | 116.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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