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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(goe570-il) GOE 570 AIRFOIL | Gottingen 570 airfoil Max thickness 33.7% at 30% chord Max camber 9.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe549-il) GOE 549 AIRFOIL | Gottingen 549 airfoil Max thickness 13.9% at 30% chord Max camber 4.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe575-il) GOE 575 AIRFOIL | Gottingen 575 airfoil Max thickness 13.3% at 29.8% chord Max camber 3.6% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe570-il,goe549-il,goe575-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe570-il | 50,000 | 9 | 0.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 50,000 | 5 | 2.5 at α=-14° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 100,000 | 9 | 7.1 at α=-12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 100,000 | 5 | 6.3 at α=-14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 200,000 | 9 | 7.8 at α=-14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 200,000 | 5 | 10.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 500,000 | 9 | 23.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 500,000 | 5 | 15.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe570-il | 1,000,000 | 9 | 20.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe570-il | 1,000,000 | 5 | 16.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe549-il | 50,000 | 9 | 7.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe549-il | 50,000 | 5 | 26.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe549-il | 100,000 | 9 | 43 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe549-il | 100,000 | 5 | 52.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe549-il | 200,000 | 9 | 74.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe549-il | 200,000 | 5 | 75.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe549-il | 500,000 | 9 | 107.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe549-il | 500,000 | 5 | 100.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe549-il | 1,000,000 | 9 | 128.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe549-il | 1,000,000 | 5 | 115.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 50,000 | 9 | 31.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 50,000 | 5 | 32.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 100,000 | 9 | 47.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 100,000 | 5 | 44.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 200,000 | 9 | 57.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 200,000 | 5 | 55.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 500,000 | 9 | 74.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 500,000 | 5 | 70.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe575-il | 1,000,000 | 9 | 88.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe575-il | 1,000,000 | 5 | 75.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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