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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(goe422-il) GOE 422 AIRFOIL | Gottingen 422 airfoil Max thickness 17.1% at 29.5% chord Max camber 6.5% at 39.5% chord | Remove Airfoil details Airfoil plotter |
(ag19-il) AG19 | Drela AG19 airfoil Max thickness 5.4% at 20.6% chord Max camber 2.2% at 44.2% chord | Remove Airfoil details Airfoil plotter |
(goe456-il) GOE 456 AIRFOIL | Gottingen 456 airfoil Max thickness 7.2% at 29.9% chord Max camber 5.2% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe427-il) GOE 427 AIRFOIL | Gottingen 427 airfoil Max thickness 4.6% at 20% chord Max camber 5.4% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe422-il,ag19-il,goe456-il,goe427-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe422-il | 50,000 | 9 | 5.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe422-il | 50,000 | 5 | 19.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe422-il | 100,000 | 9 | 44.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe422-il | 100,000 | 5 | 47.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe422-il | 200,000 | 9 | 71 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe422-il | 200,000 | 5 | 66.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe422-il | 500,000 | 9 | 97.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe422-il | 500,000 | 5 | 85.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe422-il | 1,000,000 | 9 | 117.3 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe422-il | 1,000,000 | 5 | 98.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 50,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 50,000 | 5 | 37.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 100,000 | 9 | 51.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 100,000 | 5 | 48.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 200,000 | 9 | 66.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 200,000 | 5 | 60.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 500,000 | 9 | 81.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 500,000 | 5 | 77.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag19-il | 1,000,000 | 9 | 95.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag19-il | 1,000,000 | 5 | 90.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe456-il | 50,000 | 9 | 42.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe456-il | 50,000 | 5 | 42.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe456-il | 100,000 | 9 | 65.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe456-il | 100,000 | 5 | 64.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe456-il | 200,000 | 9 | 87.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe456-il | 200,000 | 5 | 86.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe456-il | 500,000 | 9 | 117.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe456-il | 500,000 | 5 | 115.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe456-il | 1,000,000 | 9 | 140.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe456-il | 1,000,000 | 5 | 134.3 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 50,000 | 9 | 45.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 50,000 | 5 | 46.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 100,000 | 9 | 66.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 100,000 | 5 | 67.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 200,000 | 9 | 89 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 200,000 | 5 | 86.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 500,000 | 9 | 114.4 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 500,000 | 5 | 94.7 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe427-il | 1,000,000 | 9 | 122.8 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe427-il | 1,000,000 | 5 | 95 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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