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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(goe367-il) GOE 367 AIRFOIL | Gottingen 367 airfoil Max thickness 16.3% at 29.7% chord Max camber 4.6% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(goe382-il) GOE 382 AIRFOIL | Gottingen 382 airfoil Max thickness 20% at 29% chord Max camber 6% at 39% chord | Remove Airfoil details Airfoil plotter |
(goe496-il) GOE 496 AIRFOIL | Gottingen 496 airfoil Max thickness 10% at 30% chord Max camber 5% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe367-il,goe382-il,goe496-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe367-il | 50,000 | 9 | 5.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 50,000 | 5 | 20.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 100,000 | 9 | 41.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 100,000 | 5 | 47.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 200,000 | 9 | 68 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 200,000 | 5 | 64.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 500,000 | 9 | 93.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 500,000 | 5 | 83.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe367-il | 1,000,000 | 9 | 111.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe367-il | 1,000,000 | 5 | 98.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe382-il | 50,000 | 9 | 3.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe382-il | 50,000 | 5 | 14 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe382-il | 100,000 | 9 | 25.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe382-il | 100,000 | 5 | 39.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe382-il | 200,000 | 9 | 60.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe382-il | 200,000 | 5 | 59.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe382-il | 500,000 | 9 | 87 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe382-il | 500,000 | 5 | 81.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe382-il | 1,000,000 | 9 | 109.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe382-il | 1,000,000 | 5 | 103.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe496-il | 50,000 | 9 | 37.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe496-il | 50,000 | 5 | 41 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe496-il | 100,000 | 9 | 62.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe496-il | 100,000 | 5 | 65 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe496-il | 200,000 | 9 | 89.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe496-il | 200,000 | 5 | 87.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe496-il | 500,000 | 9 | 124.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe496-il | 500,000 | 5 | 115.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe496-il | 1,000,000 | 9 | 150.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe496-il | 1,000,000 | 5 | 124 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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