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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(fx601001-il) FX 60-100 (126) AIRFOIL | Wortmann FX 60-100 (126) airfoil Max thickness 10.1% at 30.8% chord Max camber 3.6% at 59.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx601001-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx601001-il | 50,000 | 9 | 38.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 50,000 | 5 | 42.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 100,000 | 9 | 61 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 100,000 | 5 | 62.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 200,000 | 9 | 84.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 200,000 | 5 | 76.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 500,000 | 9 | 103 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 500,000 | 5 | 92.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx601001-il | 1,000,000 | 9 | 116.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx601001-il | 1,000,000 | 5 | 101.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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