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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(fx6617a2-il) FX 66-17AII-182 AIRFOIL | Wortmann FX 66-17AII-182 airfoil Max thickness 18.2% at 33.9% chord Max camber 3.8% at 37.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx6617a2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx6617a2-il | 50,000 | 9 | 4.6 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 50,000 | 5 | 8.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 100,000 | 9 | 5.9 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 100,000 | 5 | 29.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 200,000 | 9 | 65 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 200,000 | 5 | 67.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 500,000 | 9 | 104.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 500,000 | 5 | 102 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617a2-il | 1,000,000 | 9 | 131.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617a2-il | 1,000,000 | 5 | 125.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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