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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(fx63137-il) WORTMANN FX 63-137 AIRFOIL | Wortmann FX 63-137 human power aircraft airfoil (Liver Puffin) airfoil Max thickness 13.7% at 30.9% chord Max camber 6% at 53.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx63137-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx63137-il | 50,000 | 9 | 26.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 50,000 | 5 | 31.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 100,000 | 9 | 62.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 100,000 | 5 | 63.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 200,000 | 9 | 90.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 200,000 | 5 | 85.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 500,000 | 9 | 119.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 500,000 | 5 | 103.6 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx63137-il | 1,000,000 | 9 | 132.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx63137-il | 1,000,000 | 5 | 105.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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