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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(fxl142k-il) FX LIII-142 K 25 AIRFOIL | Wortmann FX LIII-142 K 25 airfoil Max thickness 14.2% at 30.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fxl142k-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fxl142k-il | 50,000 | 9 | 27.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxl142k-il | 50,000 | 5 | 28.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxl142k-il | 100,000 | 9 | 42.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxl142k-il | 100,000 | 5 | 39.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxl142k-il | 200,000 | 9 | 54.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxl142k-il | 200,000 | 5 | 47.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxl142k-il | 500,000 | 9 | 63.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxl142k-il | 500,000 | 5 | 60.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fxl142k-il | 1,000,000 | 9 | 75.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fxl142k-il | 1,000,000 | 5 | 72.1 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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