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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(goe562-il) GOE 562 AIRFOIL | Gottingen 562 airfoil Max thickness 14.1% at 30% chord Max camber 6.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe528-il) GOE 528 AIRFOIL | Gottingen 528 airfoil Max thickness 12.5% at 29.8% chord Max camber 6.2% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(goe54-il) GOE 54 AIRFOIL | Gottingen 54 airfoil Max thickness 6.5% at 14.9% chord Max camber 3.5% at 19.9% 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 |
(goe563-il) GOE 563 AIRFOIL | Gottingen 563 airfoil Max thickness 8.9% at 29.8% chord Max camber 2.2% at 49.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe562-il,goe528-il,goe54-il,goe573-il,goe563-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe562-il | 50,000 | 9 | 9.2 at α=-4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 50,000 | 5 | 25.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 100,000 | 9 | 40.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 100,000 | 5 | 50 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 200,000 | 9 | 70.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 200,000 | 5 | 70.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 500,000 | 9 | 101.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 500,000 | 5 | 96.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe562-il | 1,000,000 | 9 | 126.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe562-il | 1,000,000 | 5 | 115.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe528-il | 50,000 | 9 | 9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe528-il | 50,000 | 5 | 29.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe528-il | 100,000 | 9 | 46.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe528-il | 100,000 | 5 | 55.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe528-il | 200,000 | 9 | 75.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe528-il | 200,000 | 5 | 77.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe528-il | 500,000 | 9 | 110.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe528-il | 500,000 | 5 | 106.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe528-il | 1,000,000 | 9 | 137.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe528-il | 1,000,000 | 5 | 128.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe54-il | 50,000 | 9 | 19.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe54-il | 50,000 | 5 | 29.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe54-il | 100,000 | 9 | 34.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe54-il | 100,000 | 5 | 44.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe54-il | 200,000 | 9 | 58.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe54-il | 200,000 | 5 | 64.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe54-il | 500,000 | 9 | 87.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe54-il | 500,000 | 5 | 88.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe54-il | 1,000,000 | 9 | 106.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe54-il | 1,000,000 | 5 | 105.7 at α=8.5° | 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 | |
| goe563-il | 50,000 | 9 | 35.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe563-il | 50,000 | 5 | 36.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe563-il | 100,000 | 9 | 54.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe563-il | 100,000 | 5 | 51 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe563-il | 200,000 | 9 | 73.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe563-il | 200,000 | 5 | 64.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe563-il | 500,000 | 9 | 95.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe563-il | 500,000 | 5 | 76.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe563-il | 1,000,000 | 9 | 105.6 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe563-il | 1,000,000 | 5 | 86.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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