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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(fx80080-il) WORTMANN FX 80-080 | Wortmann FX 80-080 airfoil Max thickness 8.1% at 40.2% chord Max camber 2.2% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx80080-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx80080-il | 50,000 | 9 | 33.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx80080-il | 50,000 | 5 | 36.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx80080-il | 100,000 | 9 | 57.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx80080-il | 100,000 | 5 | 55.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx80080-il | 200,000 | 9 | 80.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx80080-il | 200,000 | 5 | 74.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx80080-il | 500,000 | 9 | 113.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx80080-il | 500,000 | 5 | 90.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx80080-il | 1,000,000 | 9 | 123.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx80080-il | 1,000,000 | 5 | 98 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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