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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(fx75vg166-il) FX 75-VG-166/22 | Wortmann FX 75-VG-166/22 variable geometry airfoil Max thickness 16.7% at 43.5% chord Max camber 2.4% at 40.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx75vg166-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx75vg166-il | 50,000 | 9 | 20.6 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75vg166-il | 50,000 | 5 | 17.2 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75vg166-il | 100,000 | 9 | 28.7 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75vg166-il | 100,000 | 5 | 25.7 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75vg166-il | 200,000 | 9 | 43.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75vg166-il | 200,000 | 5 | 45 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75vg166-il | 500,000 | 9 | 82.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75vg166-il | 500,000 | 5 | 84 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx75vg166-il | 1,000,000 | 9 | 107.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx75vg166-il | 1,000,000 | 5 | 103.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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