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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(e625-il) EPPLER 625 AIRFOIL | Eppler E625 airfoil Max thickness 13% at 30% chord Max camber 2.9% at 22.5% chord | Remove Airfoil details Airfoil plotter |
(goe548-il) GOE 548 AIRFOIL | Gottingen 548 airfoil Max thickness 11.9% at 40% chord Max camber 2.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe509-il) GOE 509 AIRFOIL | Gottingen 509 airfoil Max thickness 11.1% at 29.9% chord Max camber 5.2% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(e328-il) EPPLER 328 AIRFOIL | Eppler E328 flying wing airfoil Max thickness 13.3% at 31.5% chord Max camber 3% at 22.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e625-il,goe548-il,goe509-il,e328-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e625-il | 50,000 | 9 | 18.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e625-il | 50,000 | 5 | 28.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e625-il | 100,000 | 9 | 39.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e625-il | 100,000 | 5 | 44.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e625-il | 200,000 | 9 | 58 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e625-il | 200,000 | 5 | 60.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e625-il | 500,000 | 9 | 82.9 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e625-il | 500,000 | 5 | 76.5 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e625-il | 1,000,000 | 9 | 96.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e625-il | 1,000,000 | 5 | 93.2 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe548-il | 50,000 | 9 | 34.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe548-il | 50,000 | 5 | 32.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe548-il | 100,000 | 9 | 53.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe548-il | 100,000 | 5 | 51.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe548-il | 200,000 | 9 | 74.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe548-il | 200,000 | 5 | 68.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe548-il | 500,000 | 9 | 95 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe548-il | 500,000 | 5 | 76.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe548-il | 1,000,000 | 9 | 100.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe548-il | 1,000,000 | 5 | 76.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 50,000 | 9 | 19.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 50,000 | 5 | 35.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 100,000 | 9 | 51.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 100,000 | 5 | 52.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 200,000 | 9 | 69.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 200,000 | 5 | 68.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 500,000 | 9 | 96.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 500,000 | 5 | 91.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 1,000,000 | 9 | 117.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 1,000,000 | 5 | 97.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e328-il | 50,000 | 9 | 17.6 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e328-il | 50,000 | 5 | 27.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e328-il | 100,000 | 9 | 37.7 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e328-il | 100,000 | 5 | 46.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e328-il | 200,000 | 9 | 63.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e328-il | 200,000 | 5 | 63.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e328-il | 500,000 | 9 | 88.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e328-il | 500,000 | 5 | 86.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e328-il | 1,000,000 | 9 | 111.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e328-il | 1,000,000 | 5 | 105.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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