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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(goe615-il) GOE 615 AIRFOIL | Gottingen 615 airfoil Max thickness 13.7% at 29.7% chord Max camber 5.6% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(goe620-il) GOE 620 AIRFOIL | Gottingen 620 airfoil Max thickness 17.5% at 30% chord Max camber 5.9% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe627-il) GOE 627 AIRFOIL | Gottingen 627 airfoil Max thickness 15.8% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe615-il,goe620-il,goe627-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe615-il | 50,000 | 9 | 10.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 50,000 | 5 | 30.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 100,000 | 9 | 51 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 100,000 | 5 | 53 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 200,000 | 9 | 74.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 200,000 | 5 | 72.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 500,000 | 9 | 104.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 500,000 | 5 | 93.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe615-il | 1,000,000 | 9 | 125.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe615-il | 1,000,000 | 5 | 102.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 50,000 | 9 | 4.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 50,000 | 5 | 14.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 100,000 | 9 | 42.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 100,000 | 5 | 43.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 200,000 | 9 | 71.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 200,000 | 5 | 64.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 500,000 | 9 | 97.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 500,000 | 5 | 82.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 1,000,000 | 9 | 117.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 1,000,000 | 5 | 87.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe627-il | 50,000 | 9 | 25.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe627-il | 50,000 | 5 | 29.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe627-il | 100,000 | 9 | 43.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe627-il | 100,000 | 5 | 41.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe627-il | 200,000 | 9 | 55.2 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe627-il | 200,000 | 5 | 52.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe627-il | 500,000 | 9 | 74.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe627-il | 500,000 | 5 | 71.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe627-il | 1,000,000 | 9 | 93.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe627-il | 1,000,000 | 5 | 90.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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