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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(e521-il) EPPLER 521 AIRFOIL | Eppler E521 tailplane airfoil Max thickness 13.8% at 37% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e521-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e521-il | 50,000 | 9 | 29.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 50,000 | 5 | 29.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 100,000 | 9 | 43.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 100,000 | 5 | 34.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 200,000 | 9 | 44.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 200,000 | 5 | 43.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 500,000 | 9 | 58.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 500,000 | 5 | 56.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e521-il | 1,000,000 | 9 | 70 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e521-il | 1,000,000 | 5 | 66.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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