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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(goe289-il) GOE 289 (MVA 289) AIRFOIL | Gottingen 289 (MVA 289) airfoil Max thickness 16.8% at 30% chord Max camber 6.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe235-il) GOE 235 (SCHTTE-LANZ) AIRFOIL | Gottingen 235 (SCHATTE-LANZ) airfoil Max thickness 6.5% at 19.9% chord Max camber 3.5% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe298-il) GOE 298 AIRFOIL | Gottingen 298 airfoil Max thickness 12.8% at 19.6% chord Max camber 4.5% at 39.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe289-il,goe235-il,goe298-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe289-il | 50,000 | 9 | 4.3 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe289-il | 50,000 | 5 | 20.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe289-il | 100,000 | 9 | 38.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe289-il | 100,000 | 5 | 46.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe289-il | 200,000 | 9 | 65.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe289-il | 200,000 | 5 | 64.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe289-il | 500,000 | 9 | 92.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe289-il | 500,000 | 5 | 87.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe289-il | 1,000,000 | 9 | 115.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe289-il | 1,000,000 | 5 | 109.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 50,000 | 9 | 36.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 50,000 | 5 | 37.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 100,000 | 9 | 52.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 100,000 | 5 | 48 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 200,000 | 9 | 60.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 200,000 | 5 | 57.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 500,000 | 9 | 73.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 500,000 | 5 | 68.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe235-il | 1,000,000 | 9 | 80.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe235-il | 1,000,000 | 5 | 81.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe298-il | 50,000 | 9 | 27.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe298-il | 50,000 | 5 | 35.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe298-il | 100,000 | 9 | 52.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe298-il | 100,000 | 5 | 52.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe298-il | 200,000 | 9 | 71.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe298-il | 200,000 | 5 | 65.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe298-il | 500,000 | 9 | 91.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe298-il | 500,000 | 5 | 88.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe298-il | 1,000,000 | 9 | 112.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe298-il | 1,000,000 | 5 | 103.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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