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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(fx68h120-il) FX 68-H-120 | Wortmann FX 68-H-120 airfoil Max thickness 11.8% at 25% chord Max camber 2.3% at 33.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx68h120-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx68h120-il | 50,000 | 9 | 28.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 50,000 | 5 | 29.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 100,000 | 9 | 40.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 100,000 | 5 | 41 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 200,000 | 9 | 54.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 200,000 | 5 | 54.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 500,000 | 9 | 74.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 500,000 | 5 | 73.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx68h120-il | 1,000,000 | 9 | 91.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx68h120-il | 1,000,000 | 5 | 88.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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