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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(e862-il) EPPLER 862 STRUT AIRFOIL | Eppler E862 strut airfoil Max thickness 32.4% at 28.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e862-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e862-il | 50,000 | 9 | 2.8 at α=-4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 50,000 | 5 | 2.6 at α=-2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 100,000 | 9 | 5.1 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 100,000 | 5 | 10.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 200,000 | 9 | 20.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 200,000 | 5 | 32.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 500,000 | 9 | 57.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 500,000 | 5 | 54.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 1,000,000 | 9 | 78.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 1,000,000 | 5 | 74.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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