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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(la5055-il) LIEBECK LA5055 AIRFOIL | Liebeck high lift airfoil Max thickness 15.9% at 35% chord Max camber 5.9% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (la5055-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| la5055-il | 50,000 | 9 | 4.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 50,000 | 5 | 8.7 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 100,000 | 9 | 18.7 at α=15.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 100,000 | 5 | 15.5 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 200,000 | 9 | 24.7 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 200,000 | 5 | 46.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 500,000 | 9 | 116.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 500,000 | 5 | 104.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la5055-il | 1,000,000 | 9 | 149.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la5055-il | 1,000,000 | 5 | 83.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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