Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(goe137-il) GOE 137 (MVA H.15) AIRFOIL | Gottingen 137 (MVA H.15) airfoil Max thickness 8.6% at 29.9% chord Max camber 4.4% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe482-il) GOE 482 AIRFOIL | Gottingen 482 airfoil Max thickness 16.5% at 29.6% chord Max camber 8.8% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(goe595-il) GOE 595 AIRFOIL | Gottingen 595 airfoil Max thickness 9.6% at 30% chord Max camber 3% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe222-il) GOE 222 (MVA H.33) AIRFOIL | Gottingen 222 (MVA H.33) airfoil Max thickness 18.5% at 29.2% chord Max camber 7.2% at 49.2% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (goe137-il,goe482-il,goe595-il,goe222-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe137-il | 50,000 | 9 | 35.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe137-il | 50,000 | 5 | 39.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe137-il | 100,000 | 9 | 56.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe137-il | 100,000 | 5 | 59.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe137-il | 200,000 | 9 | 78.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe137-il | 200,000 | 5 | 77.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe137-il | 500,000 | 9 | 104.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe137-il | 500,000 | 5 | 97.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe137-il | 1,000,000 | 9 | 120.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe137-il | 1,000,000 | 5 | 109.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe482-il | 50,000 | 9 | 4.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe482-il | 50,000 | 5 | 17.3 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe482-il | 100,000 | 9 | 35.8 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe482-il | 100,000 | 5 | 51 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe482-il | 200,000 | 9 | 71.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe482-il | 200,000 | 5 | 73.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe482-il | 500,000 | 9 | 107.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe482-il | 500,000 | 5 | 100.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe482-il | 1,000,000 | 9 | 137.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe482-il | 1,000,000 | 5 | 121.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe595-il | 50,000 | 9 | 36.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe595-il | 50,000 | 5 | 38.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe595-il | 100,000 | 9 | 55.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe595-il | 100,000 | 5 | 54.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe595-il | 200,000 | 9 | 74.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe595-il | 200,000 | 5 | 68.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe595-il | 500,000 | 9 | 97.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe595-il | 500,000 | 5 | 86.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe595-il | 1,000,000 | 9 | 110.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe595-il | 1,000,000 | 5 | 100.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 50,000 | 9 | 5.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 50,000 | 5 | 14.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 100,000 | 9 | 42.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 100,000 | 5 | 47.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 200,000 | 9 | 74.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 200,000 | 5 | 67.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 500,000 | 9 | 99.2 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 500,000 | 5 | 84.8 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe222-il | 1,000,000 | 9 | 115.2 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe222-il | 1,000,000 | 5 | 102 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||