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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(goe646-il) GOE 646 AIRFOIL | Gottingen 646 airfoil Max thickness 18.3% at 29% chord Max camber 4.5% at 49% chord | Remove Airfoil details Airfoil plotter |
(goe647-il) GOE 647 AIRFOIL | Gottingen 647 airfoil Max thickness 16.2% at 19.5% chord Max camber 5.3% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(goe735-il) GOE 735 AIRFOIL | Gottingen 735 airfoil Max thickness 20.1% at 30% chord Max camber 4.4% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe801-il) GOE 801 (MVA 301) AIRFOIL | Gottingen 801 (MVA 301) airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% 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 (goe646-il,goe647-il,goe735-il,goe801-il,goe682-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe646-il | 50,000 | 9 | 5.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 50,000 | 5 | 18.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 100,000 | 9 | 43.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 100,000 | 5 | 46.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 200,000 | 9 | 68.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 200,000 | 5 | 65.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 500,000 | 9 | 95.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 500,000 | 5 | 77.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe646-il | 1,000,000 | 9 | 105.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe646-il | 1,000,000 | 5 | 85.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 50,000 | 9 | 13.1 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 50,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 100,000 | 9 | 41.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 100,000 | 5 | 44.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 200,000 | 9 | 59 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 200,000 | 5 | 58.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 500,000 | 9 | 81.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 500,000 | 5 | 81.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe647-il | 1,000,000 | 9 | 105.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe647-il | 1,000,000 | 5 | 104.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe735-il | 50,000 | 9 | 2.9 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe735-il | 50,000 | 5 | 16.4 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe735-il | 100,000 | 9 | 23.4 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe735-il | 100,000 | 5 | 35.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe735-il | 200,000 | 9 | 49.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe735-il | 200,000 | 5 | 55.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe735-il | 500,000 | 9 | 82.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe735-il | 500,000 | 5 | 78.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe735-il | 1,000,000 | 9 | 105 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe735-il | 1,000,000 | 5 | 97.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe801-il | 50,000 | 9 | 17.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe801-il | 50,000 | 5 | 38.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe801-il | 100,000 | 9 | 55.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe801-il | 100,000 | 5 | 60.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe801-il | 200,000 | 9 | 79.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe801-il | 200,000 | 5 | 79.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe801-il | 500,000 | 9 | 110.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe801-il | 500,000 | 5 | 104.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe801-il | 1,000,000 | 9 | 132 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe801-il | 1,000,000 | 5 | 123 at α=5.5° | 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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