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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(fx3-il) WORTMANN FX 3 AIRFOIL | Wortmann FX 3 airfoil Max thickness 20% at 50% chord Max camber 4.2% at 75% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx3-il | 50,000 | 5 | 15.4 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 50,000 | 0 | 18.5 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 100,000 | 5 | 23.4 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 100,000 | 0 | 23.4 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 200,000 | 5 | 32.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 200,000 | 0 | 31.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 500,000 | 5 | 44.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 500,000 | 0 | 40.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 1,000,000 | 5 | 58.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 1,000,000 | 0 | 54.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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