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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(e863-il) EPPLER 863 STRUT AIRFOIL | Eppler E863 strut airfoil Max thickness 35.7% at 28.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e863-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e863-il | 50,000 | 9 | 2.5 at α=-7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e863-il | 50,000 | 5 | 3.6 at α=-2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e863-il | 100,000 | 9 | 4.5 at α=-2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e863-il | 100,000 | 5 | 4 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e863-il | 200,000 | 9 | 8.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e863-il | 200,000 | 5 | 24 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e863-il | 500,000 | 9 | 48.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e863-il | 500,000 | 5 | 44 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e863-il | 1,000,000 | 9 | 64.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e863-il | 1,000,000 | 5 | 62 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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