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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(goe584-il) GOE 584 AIRFOIL | Gottingen 584 airfoil Max thickness 12.7% at 30% chord Max camber 5% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe518-il) GOE 518 AIRFOIL | Gottingen 518 airfoil Max thickness 18% at 29.8% chord Max camber 7.3% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(goe550-il) GOE 550 AIRFOIL | Gottingen 550 airfoil Max thickness 13% at 20% chord Max camber 4.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe584-il,goe518-il,goe550-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe584-il | 50,000 | 9 | 8.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 50,000 | 5 | 26 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 100,000 | 9 | 51.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 100,000 | 5 | 55 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 200,000 | 9 | 78.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 200,000 | 5 | 77.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 500,000 | 9 | 112.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 500,000 | 5 | 106 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 1,000,000 | 9 | 137.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 1,000,000 | 5 | 126.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe518-il | 50,000 | 9 | 6.5 at α=-3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe518-il | 50,000 | 5 | 23.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe518-il | 100,000 | 9 | 41.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe518-il | 100,000 | 5 | 39.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe518-il | 200,000 | 9 | 54.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe518-il | 200,000 | 5 | 48.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe518-il | 500,000 | 9 | 64.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe518-il | 500,000 | 5 | 61.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe518-il | 1,000,000 | 9 | 81 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe518-il | 1,000,000 | 5 | 79.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 50,000 | 9 | 27.6 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 50,000 | 5 | 33.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 100,000 | 9 | 53.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 100,000 | 5 | 56.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 200,000 | 9 | 76.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 200,000 | 5 | 75.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 500,000 | 9 | 106.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 500,000 | 5 | 98.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe550-il | 1,000,000 | 9 | 127.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe550-il | 1,000,000 | 5 | 114.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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