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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(fx66s161-il) FX 66-S-161 AIRFOIL | Wortmann FX 66-S-161 airfoil Max thickness 16.1% at 33.9% chord Max camber 3.9% at 43.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx66s161-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx66s161-il | 50,000 | 9 | 5.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 50,000 | 5 | 16.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 100,000 | 9 | 16.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 100,000 | 5 | 42.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 200,000 | 9 | 73.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 200,000 | 5 | 75.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 500,000 | 9 | 116 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 500,000 | 5 | 114.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx66s161-il | 1,000,000 | 9 | 148.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx66s161-il | 1,000,000 | 5 | 134.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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