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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(goe796-il) GOE 796 AIRFOIL | Gottingen 796 airfoil Max thickness 12% at 30% chord Max camber 3.6% at 40% 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 |
(gs1-il) SIKORSKY GS-1 AIRFOIL | Gluharoff/Sikorsky GS-1 airfoil Max thickness 13.9% at 30% chord Max camber 4.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe804-il) GOE 804 (EA 8) AIRFOIL | Gottingen 804 (EA 8) airfoil Max thickness 6% at 40% chord Max camber 6.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe796-il,goe801-il,gs1-il,goe804-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe796-il | 50,000 | 9 | 32.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 50,000 | 5 | 35.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 100,000 | 9 | 55.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 100,000 | 5 | 55.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 200,000 | 9 | 78 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 200,000 | 5 | 73.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 500,000 | 9 | 105.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 500,000 | 5 | 90.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe796-il | 1,000,000 | 9 | 122.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe796-il | 1,000,000 | 5 | 105.2 at α=4.75° | 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 | |
| gs1-il | 50,000 | 9 | 9.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 50,000 | 5 | 29.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 100,000 | 9 | 51 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 100,000 | 5 | 54.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 200,000 | 9 | 74.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 200,000 | 5 | 74.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 500,000 | 9 | 105.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 500,000 | 5 | 100.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| gs1-il | 1,000,000 | 9 | 129.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| gs1-il | 1,000,000 | 5 | 119.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe804-il | 50,000 | 9 | 43.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe804-il | 50,000 | 5 | 41.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe804-il | 100,000 | 9 | 70.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe804-il | 100,000 | 5 | 67.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe804-il | 200,000 | 9 | 107.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe804-il | 200,000 | 5 | 107 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe804-il | 500,000 | 9 | 169.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe804-il | 500,000 | 5 | 157.3 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe804-il | 1,000,000 | 9 | 211.4 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe804-il | 1,000,000 | 5 | 147 at α=0° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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