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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(la2573a-il) LA2573A | Liebeck LA2573A airfoil Max thickness 13.7% at 28.8% chord Max camber 3.2% at 26.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (la2573a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| la2573a-il | 50,000 | 9 | 6.9 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 50,000 | 5 | 13.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 100,000 | 9 | 15.7 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 100,000 | 5 | 27.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 200,000 | 9 | 62.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 200,000 | 5 | 64.9 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 500,000 | 9 | 102.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 500,000 | 5 | 95.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| la2573a-il | 1,000,000 | 9 | 125.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| la2573a-il | 1,000,000 | 5 | 110.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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