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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(e338-il) EPPLER 338 AIRFOIL | Eppler E338 flying wing airfoil Max thickness 13.3% at 31.1% chord Max camber 3.7% at 26.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e338-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e338-il | 50,000 | 9 | 15.8 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e338-il | 50,000 | 5 | 26.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e338-il | 100,000 | 9 | 33.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e338-il | 100,000 | 5 | 45.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e338-il | 200,000 | 9 | 63.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e338-il | 200,000 | 5 | 67.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e338-il | 500,000 | 9 | 97.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e338-il | 500,000 | 5 | 88.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e338-il | 1,000,000 | 9 | 114 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e338-il | 1,000,000 | 5 | 108.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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