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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(goe239-il) GOE 239 (MVA H.31) AIRFOIL | Gottingen 239 (MVA H.31) airfoil Max thickness 11.2% at 19.8% chord Max camber 6% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(goe241-il) GOE 241 (MVA PR.1) AIRFOIL | Gottingen 241 (MVA PR.1) airfoil Max thickness 18.9% at 29.5% chord Max camber 8.4% at 49.5% chord | Remove Airfoil details Airfoil plotter |
(goe229-il) GOE 229 (MVA H.39) AIRFOIL | Gottingen 229 (MVA H.39) airfoil Max thickness 19.3% at 29% chord Max camber 5.9% at 49.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe239-il,goe241-il,goe229-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe239-il | 50,000 | 9 | 17.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe239-il | 50,000 | 5 | 38.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe239-il | 100,000 | 9 | 54.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe239-il | 100,000 | 5 | 60.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe239-il | 200,000 | 9 | 81.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe239-il | 200,000 | 5 | 83.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe239-il | 500,000 | 9 | 118.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe239-il | 500,000 | 5 | 113 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe239-il | 1,000,000 | 9 | 144.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe239-il | 1,000,000 | 5 | 125.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe241-il | 50,000 | 9 | 4.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe241-il | 50,000 | 5 | 18.8 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe241-il | 100,000 | 9 | 42.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe241-il | 100,000 | 5 | 49 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe241-il | 200,000 | 9 | 68.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe241-il | 200,000 | 5 | 67.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe241-il | 500,000 | 9 | 94.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe241-il | 500,000 | 5 | 91.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe241-il | 1,000,000 | 9 | 120.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe241-il | 1,000,000 | 5 | 113.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 50,000 | 9 | 10.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 50,000 | 5 | 21.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 100,000 | 9 | 45.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 100,000 | 5 | 38.5 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 200,000 | 9 | 53.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 200,000 | 5 | 40.9 at α=-0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 500,000 | 9 | 54.8 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 500,000 | 5 | 47.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe229-il | 1,000,000 | 9 | 59.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe229-il | 1,000,000 | 5 | 59.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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