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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(fx6617ai-il) WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) | Wortmann FX 66-17AII-182 airfoil (as tested at NASA) Max thickness 18.8% at 35.3% chord Max camber 3.7% at 40.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx6617ai-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx6617ai-il | 50,000 | 9 | 4.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 50,000 | 5 | 8.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 100,000 | 9 | 6.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 100,000 | 5 | 29.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 200,000 | 9 | 62.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 200,000 | 5 | 68.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 500,000 | 9 | 109.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 500,000 | 5 | 105.5 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx6617ai-il | 1,000,000 | 9 | 137.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx6617ai-il | 1,000,000 | 5 | 130.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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