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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(goe226-il) GOE 226 (MVA H.36) AIRFOIL | Gottingen 226 (MVA H.36) airfoil Max thickness 13.9% at 19.7% chord Max camber 8.1% at 49.7% chord | Remove Airfoil details Airfoil plotter |
(goe210-il) GOE 210 (DAIMLER) AIRFOIL | Gottingen 210 (DAIMLER) airfoil Max thickness 6.6% at 30% chord Max camber 4.3% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe207-il) GOE 207 (AVIATIK V8) AIRFOIL | Gottingen 207 (AVIATIK V8) airfoil Max thickness 8.8% at 19.9% chord Max camber 6.6% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(goe240-il) GOE 240 (KOLLER) AIRFOIL | Gottingen 240 (KOLLER) airfoil Max thickness 7% at 29.9% chord Max camber 5.2% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe226-il,goe210-il,goe207-il,goe240-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe226-il | 50,000 | 9 | 8.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe226-il | 50,000 | 5 | 28.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe226-il | 100,000 | 9 | 52.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe226-il | 100,000 | 5 | 59.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe226-il | 200,000 | 9 | 85.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe226-il | 200,000 | 5 | 78.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe226-il | 500,000 | 9 | 109.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe226-il | 500,000 | 5 | 102.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe226-il | 1,000,000 | 9 | 135.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe226-il | 1,000,000 | 5 | 125.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 50,000 | 9 | 40.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 50,000 | 5 | 43.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 100,000 | 9 | 62 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 100,000 | 5 | 62 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 200,000 | 9 | 82.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 200,000 | 5 | 77.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 500,000 | 9 | 105.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 500,000 | 5 | 86.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 1,000,000 | 9 | 116.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 1,000,000 | 5 | 99.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe207-il | 50,000 | 9 | 20.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe207-il | 50,000 | 5 | 33.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe207-il | 100,000 | 9 | 47.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe207-il | 100,000 | 5 | 52 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe207-il | 200,000 | 9 | 70.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe207-il | 200,000 | 5 | 71.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe207-il | 500,000 | 9 | 99.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe207-il | 500,000 | 5 | 96.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe207-il | 1,000,000 | 9 | 120.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe207-il | 1,000,000 | 5 | 113.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe240-il | 50,000 | 9 | 37.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe240-il | 50,000 | 5 | 43.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe240-il | 100,000 | 9 | 62.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe240-il | 100,000 | 5 | 62.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe240-il | 200,000 | 9 | 83.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe240-il | 200,000 | 5 | 78.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe240-il | 500,000 | 9 | 107.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe240-il | 500,000 | 5 | 91.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe240-il | 1,000,000 | 9 | 121.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe240-il | 1,000,000 | 5 | 99.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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