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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(goe407-il) GOE 407 AIRFOIL | Gottingen 407 airfoil Max thickness 9.5% at 29.9% chord Max camber 4.8% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe646-il) GOE 646 AIRFOIL | Gottingen 646 airfoil Max thickness 18.3% at 29% chord Max camber 4.5% at 49% chord | Remove Airfoil details Airfoil plotter |
(goe652-il) GOE 652 AIRFOIL | Gottingen 652 airfoil Max thickness 17.1% at 20% chord Max camber 9.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe509-il) GOE 509 AIRFOIL | Gottingen 509 airfoil Max thickness 11.1% at 29.9% chord Max camber 5.2% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe407-il,goe646-il,goe652-il,goe509-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe407-il | 50,000 | 9 | 27.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe407-il | 50,000 | 5 | 37.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe407-il | 100,000 | 9 | 56.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe407-il | 100,000 | 5 | 57.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe407-il | 200,000 | 9 | 79.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe407-il | 200,000 | 5 | 75.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe407-il | 500,000 | 9 | 106.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe407-il | 500,000 | 5 | 95.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe407-il | 1,000,000 | 9 | 121.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe407-il | 1,000,000 | 5 | 114.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 50,000 | 9 | 5.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 50,000 | 5 | 18.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 100,000 | 9 | 43.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 100,000 | 5 | 46.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 200,000 | 9 | 68.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 200,000 | 5 | 65.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 500,000 | 9 | 95.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 500,000 | 5 | 77.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 1,000,000 | 9 | 105.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 1,000,000 | 5 | 85.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 50,000 | 9 | 5.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 50,000 | 5 | 21.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 100,000 | 9 | 49.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 100,000 | 5 | 53.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 200,000 | 9 | 77.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 200,000 | 5 | 78 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 500,000 | 9 | 112.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 500,000 | 5 | 102.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe652-il | 1,000,000 | 9 | 135.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe652-il | 1,000,000 | 5 | 115.7 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 50,000 | 9 | 19.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 50,000 | 5 | 35.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 100,000 | 9 | 51.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 100,000 | 5 | 52.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 200,000 | 9 | 69.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 200,000 | 5 | 68.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 500,000 | 9 | 96.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 500,000 | 5 | 91.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe509-il | 1,000,000 | 9 | 117.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe509-il | 1,000,000 | 5 | 97.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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