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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(e715-il) EPPLER 715 AIRFOIL | Eppler E715 tailplane airfoil Max thickness 15% at 33.1% chord Max camber 2.8% at 42% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e715-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e715-il | 50,000 | 9 | 5.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e715-il | 50,000 | 5 | 15.7 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e715-il | 100,000 | 9 | 43.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e715-il | 100,000 | 5 | 44.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e715-il | 200,000 | 9 | 74.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e715-il | 200,000 | 5 | 74.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e715-il | 500,000 | 9 | 113.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e715-il | 500,000 | 5 | 98 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e715-il | 1,000,000 | 9 | 136.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e715-il | 1,000,000 | 5 | 111.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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