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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(e475-il) E475 (15.01%) | Eppler E475 aerobatic aircraft airfoil Max thickness 15% at 21.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e475-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e475-il | 50,000 | 9 | 20.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 50,000 | 5 | 24.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 100,000 | 9 | 30.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 100,000 | 5 | 36.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 200,000 | 9 | 46.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 200,000 | 5 | 51.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 500,000 | 9 | 72.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 500,000 | 5 | 71 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e475-il | 1,000,000 | 9 | 90 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e475-il | 1,000,000 | 5 | 83.6 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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