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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(fx71120-il) WORTMANN FX 71-120 AIRFOIL | Wortmann FX 71-120 airfoil Max thickness 12% at 25% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx71120-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx71120-il | 50,000 | 9 | 20.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71120-il | 50,000 | 5 | 21.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71120-il | 100,000 | 9 | 26.3 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71120-il | 100,000 | 5 | 29.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71120-il | 200,000 | 9 | 34.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71120-il | 200,000 | 5 | 38.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71120-il | 500,000 | 9 | 50.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71120-il | 500,000 | 5 | 56.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx71120-il | 1,000,000 | 9 | 64.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx71120-il | 1,000,000 | 5 | 71.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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