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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(goe648-il) GOE 648 AIRFOIL | Gottingen 648 airfoil Max thickness 15.2% at 29.4% chord Max camber 3.9% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(goe675-il) GOE 675 AIRFOIL | Gottingen 675 airfoil Max thickness 14.9% at 29.5% chord Max camber 5.9% at 39.5% chord | Remove Airfoil details Airfoil plotter |
(goe681-il) GOE 681 AIRFOIL | Gottingen 681 airfoil Max thickness 16.8% at 29.2% chord Max camber 4.4% at 39.2% chord | Remove Airfoil details Airfoil plotter |
(goe650-il) GOE 650 AIRFOIL | Gottingen 650 airfoil Max thickness 13.4% at 19.5% chord Max camber 4.4% at 49.5% chord | Remove Airfoil details Airfoil plotter |
(goe682-il) GOE 682 AIRFOIL | Gottingen 682 airfoil Max thickness 10.7% at 30% chord Max camber 4.3% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe648-il,goe675-il,goe681-il,goe650-il,goe682-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe648-il | 50,000 | 9 | 22.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 50,000 | 5 | 30.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 100,000 | 9 | 43.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 100,000 | 5 | 44.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 200,000 | 9 | 57.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 200,000 | 5 | 57.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 500,000 | 9 | 79.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 500,000 | 5 | 80.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 1,000,000 | 9 | 104.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 1,000,000 | 5 | 101.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 50,000 | 9 | 8.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 50,000 | 5 | 28.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 100,000 | 9 | 51.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 100,000 | 5 | 52.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 200,000 | 9 | 75.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 200,000 | 5 | 69.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 500,000 | 9 | 104.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 500,000 | 5 | 90.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe675-il | 1,000,000 | 9 | 117.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe675-il | 1,000,000 | 5 | 111.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 50,000 | 9 | 9.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 50,000 | 5 | 26.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 100,000 | 9 | 44.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 100,000 | 5 | 42.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 200,000 | 9 | 61.7 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 200,000 | 5 | 55.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 500,000 | 9 | 79.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 500,000 | 5 | 73.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe681-il | 1,000,000 | 9 | 97.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe681-il | 1,000,000 | 5 | 94 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe650-il | 50,000 | 9 | 31.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe650-il | 50,000 | 5 | 34.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe650-il | 100,000 | 9 | 56 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe650-il | 100,000 | 5 | 53.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe650-il | 200,000 | 9 | 79 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe650-il | 200,000 | 5 | 70.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe650-il | 500,000 | 9 | 101.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe650-il | 500,000 | 5 | 83.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe650-il | 1,000,000 | 9 | 109.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe650-il | 1,000,000 | 5 | 96.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe682-il | 50,000 | 9 | 25.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe682-il | 50,000 | 5 | 37.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe682-il | 100,000 | 9 | 55.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe682-il | 100,000 | 5 | 57.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe682-il | 200,000 | 9 | 78.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe682-il | 200,000 | 5 | 75.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe682-il | 500,000 | 9 | 106.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe682-il | 500,000 | 5 | 97.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe682-il | 1,000,000 | 9 | 126.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe682-il | 1,000,000 | 5 | 112.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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