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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(e193-il) E193 (10.22%) | Eppler E193 low Reynolds number airfoil Max thickness 10.2% at 31% chord Max camber 3% at 44.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e193-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e193-il | 50,000 | 9 | 35.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e193-il | 50,000 | 5 | 35.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e193-il | 100,000 | 9 | 58.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e193-il | 100,000 | 5 | 58.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e193-il | 200,000 | 9 | 82.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e193-il | 200,000 | 5 | 80.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e193-il | 500,000 | 9 | 114.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e193-il | 500,000 | 5 | 107.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e193-il | 1,000,000 | 9 | 138.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e193-il | 1,000,000 | 5 | 125.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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