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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(fx60160-il) FX 60-160 AIRFOIL | Wortmann FX 60-160 airfoil Max thickness 15.6% at 40% chord Max camber 3.1% at 60% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx60160-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx60160-il | 50,000 | 9 | 23.4 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 50,000 | 5 | 22.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 100,000 | 9 | 51 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 100,000 | 5 | 48.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 200,000 | 9 | 72.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 200,000 | 5 | 68.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 500,000 | 9 | 96.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 500,000 | 5 | 89 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx60160-il | 1,000,000 | 9 | 116.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx60160-il | 1,000,000 | 5 | 102.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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