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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(e214-il) E214 (11.1%) | Eppler E214 low Reynolds number airfoil Max thickness 11.1% at 33.1% chord Max camber 3.7% at 56.9% chord | Remove Airfoil details Airfoil plotter |
(goe573-il) GOE 573 AIRFOIL | Gottingen 573 airfoil Max thickness 14.1% at 29.9% chord Max camber 6.5% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e214-il,goe573-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e214-il | 50,000 | 9 | 37.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e214-il | 50,000 | 5 | 39.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e214-il | 100,000 | 9 | 61.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e214-il | 100,000 | 5 | 63.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e214-il | 200,000 | 9 | 87.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e214-il | 200,000 | 5 | 84.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e214-il | 500,000 | 9 | 121.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e214-il | 500,000 | 5 | 111.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e214-il | 1,000,000 | 9 | 145.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e214-il | 1,000,000 | 5 | 122.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe573-il | 50,000 | 9 | 11.6 at α=-4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe573-il | 50,000 | 5 | 24.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe573-il | 100,000 | 9 | 34.4 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe573-il | 100,000 | 5 | 47.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe573-il | 200,000 | 9 | 64.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe573-il | 200,000 | 5 | 69.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe573-il | 500,000 | 9 | 99.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe573-il | 500,000 | 5 | 100 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe573-il | 1,000,000 | 9 | 130.2 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe573-il | 1,000,000 | 5 | 127.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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