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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(fx61168-il) FX 61-168 AIRFOIL | Wortmann FX 61-168 airfoil Max thickness 16.8% at 37.1% chord Max camber 3% at 37.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx61168-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx61168-il | 50,000 | 9 | 5.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 50,000 | 5 | 15.4 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 100,000 | 9 | 44.7 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 100,000 | 5 | 48.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 200,000 | 9 | 71 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 200,000 | 5 | 73 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 500,000 | 9 | 104.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 500,000 | 5 | 101.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx61168-il | 1,000,000 | 9 | 129.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx61168-il | 1,000,000 | 5 | 120.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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