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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(e326-il) EPPLER 326 AIRFOIL | Eppler E326 flying wing airfoil Max thickness 12.9% at 33.4% chord Max camber 2.1% at 19.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e326-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e326-il | 50,000 | 9 | 17.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e326-il | 50,000 | 5 | 26.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e326-il | 100,000 | 9 | 39.4 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e326-il | 100,000 | 5 | 44.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e326-il | 200,000 | 9 | 60.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e326-il | 200,000 | 5 | 55.5 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e326-il | 500,000 | 9 | 76.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e326-il | 500,000 | 5 | 75.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e326-il | 1,000,000 | 9 | 96.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e326-il | 1,000,000 | 5 | 90.7 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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