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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(goe217-il) GOE 217 (MVA MK.12) AIRFOIL | Gottingen 217 (MVA MK.12) airfoil Max thickness 19% at 29.2% chord Max camber 6.3% at 59.4% chord | Remove Airfoil details Airfoil plotter |
(goe255-il) GOE 255 (MVA CA.6) AIRFOIL | Gottingen 255 (MVA CA.6) airfoil Max thickness 18.5% at 29.1% chord Max camber 4.8% at 49.1% chord | Remove Airfoil details Airfoil plotter |
(goe287-il) GOE 287 AIRFOIL | Gottingen 287 airfoil Max thickness 8.9% at 29.9% chord Max camber 4.9% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe155-il) GOE 155 (SSW D.1) AIRFOIL | Gottingen 155 (SSW D.1) airfoil Max thickness 7% at 29.9% chord Max camber 5.3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe217-il,goe255-il,goe287-il,goe155-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe217-il | 50,000 | 9 | 5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 50,000 | 5 | 21.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 100,000 | 9 | 40.2 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 100,000 | 5 | 48.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 200,000 | 9 | 67 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 200,000 | 5 | 70.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 500,000 | 9 | 101.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 500,000 | 5 | 99.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe217-il | 1,000,000 | 9 | 127.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe217-il | 1,000,000 | 5 | 119.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 50,000 | 9 | 5.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 50,000 | 5 | 15.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 100,000 | 9 | 41.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 100,000 | 5 | 47.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 200,000 | 9 | 72.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 200,000 | 5 | 71.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 500,000 | 9 | 105.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 500,000 | 5 | 90.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe255-il | 1,000,000 | 9 | 127.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe255-il | 1,000,000 | 5 | 96.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 50,000 | 9 | 36.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 50,000 | 5 | 38 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 100,000 | 9 | 58.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 100,000 | 5 | 59.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 200,000 | 9 | 80 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 200,000 | 5 | 77.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 500,000 | 9 | 106.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 500,000 | 5 | 94.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe287-il | 1,000,000 | 9 | 123 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe287-il | 1,000,000 | 5 | 106.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 50,000 | 9 | 40.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 50,000 | 5 | 42.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 100,000 | 9 | 59.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 100,000 | 5 | 61.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 200,000 | 9 | 82.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 200,000 | 5 | 78.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 500,000 | 9 | 107.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 500,000 | 5 | 98.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 1,000,000 | 9 | 123.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 1,000,000 | 5 | 111 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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