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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(fxm2-il) WORTMANN FX M2 AIRFOIL | Wortmann FX M2 airfoil Max thickness 8.4% at 19.6% chord Max camber 4.8% at 30.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fxm2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fxm2-il | 50,000 | 9 | 31.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxm2-il | 50,000 | 5 | 35.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxm2-il | 100,000 | 9 | 45.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxm2-il | 100,000 | 5 | 50.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxm2-il | 200,000 | 9 | 65.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxm2-il | 200,000 | 5 | 68.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxm2-il | 500,000 | 9 | 94.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxm2-il | 500,000 | 5 | 86.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxm2-il | 1,000,000 | 9 | 103.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxm2-il | 1,000,000 | 5 | 100.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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