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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(fx66s171-il) FX 66-S-171 AIRFOIL | Wortmann FX 66-S-171 airfoil Max thickness 17.1% at 33.9% chord Max camber 3.9% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx66s171-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66s171-il | 50,000 | 9 | 5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s171-il | 50,000 | 5 | 12.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s171-il | 100,000 | 9 | 13.3 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s171-il | 100,000 | 5 | 39.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s171-il | 200,000 | 9 | 70.3 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s171-il | 200,000 | 5 | 72.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s171-il | 500,000 | 9 | 113.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s171-il | 500,000 | 5 | 113.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s171-il | 1,000,000 | 9 | 147.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s171-il | 1,000,000 | 5 | 133.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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