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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(fx61140-il) FX 61-140 AIRFOIL | Wortmann FX 61-140 airfoil Max thickness 14% at 33.9% chord Max camber 2.5% at 30.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx61140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx61140-il | 50,000 | 9 | 14.4 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 50,000 | 5 | 31.2 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 100,000 | 9 | 51.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 100,000 | 5 | 52 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 200,000 | 9 | 69.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 200,000 | 5 | 70.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 500,000 | 9 | 96.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 500,000 | 5 | 96.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61140-il | 1,000,000 | 9 | 119 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61140-il | 1,000,000 | 5 | 115.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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