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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(e168-il) E168 (12.45%) | Eppler E168 low Reynolds number airfoil Max thickness 12.4% at 26.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e168-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e168-il | 50,000 | 9 | 22.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 50,000 | 5 | 28 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 100,000 | 9 | 38.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 100,000 | 5 | 40.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 200,000 | 9 | 53.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 200,000 | 5 | 52.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 500,000 | 9 | 73 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 500,000 | 5 | 67.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 1,000,000 | 9 | 87 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 1,000,000 | 5 | 77.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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