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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(fx057816-il) WORTMANN FX 057-816 | Wortmann FX 057-816 airfoil Max thickness 16.2% at 37.1% chord Max camber 5.1% at 37.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx057816-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx057816-il | 50,000 | 9 | 5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx057816-il | 50,000 | 5 | 11.1 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx057816-il | 100,000 | 9 | 17.8 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx057816-il | 100,000 | 5 | 16.5 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx057816-il | 200,000 | 9 | 27.6 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx057816-il | 200,000 | 5 | 27.1 at α=11.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx057816-il | 500,000 | 9 | 113.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx057816-il | 500,000 | 5 | 113.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx057816-il | 1,000,000 | 9 | 155.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx057816-il | 1,000,000 | 5 | 153 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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