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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(goe777-il) GOE 777 AIRFOIL | Gottingen 777 airfoil Max thickness 22% at 30% chord Max camber 5.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe798-il) GOE 798 AIRFOIL | Gottingen 798 airfoil Max thickness 20% at 30% chord Max camber 6% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe780-il) GOE 780 AIRFOIL | Gottingen 780 airfoil Max thickness 12% at 50% chord Max camber 1% at 40% chord | Remove Airfoil details Airfoil plotter |
(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 |
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Polars for (goe777-il,goe798-il,goe780-il,goe796-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe777-il | 50,000 | 9 | 3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe777-il | 50,000 | 5 | 8.1 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe777-il | 100,000 | 9 | 15.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe777-il | 100,000 | 5 | 32.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe777-il | 200,000 | 9 | 54.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe777-il | 200,000 | 5 | 57.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe777-il | 500,000 | 9 | 90.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe777-il | 500,000 | 5 | 81.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe777-il | 1,000,000 | 9 | 109 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe777-il | 1,000,000 | 5 | 101.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe798-il | 50,000 | 9 | 3.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe798-il | 50,000 | 5 | 10.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe798-il | 100,000 | 9 | 20.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe798-il | 100,000 | 5 | 31.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe798-il | 200,000 | 9 | 65.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe798-il | 200,000 | 5 | 61.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe798-il | 500,000 | 9 | 98.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe798-il | 500,000 | 5 | 83.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe798-il | 1,000,000 | 9 | 120 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe798-il | 1,000,000 | 5 | 84.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 50,000 | 9 | 12.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 50,000 | 5 | 19.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 100,000 | 9 | 29.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 100,000 | 5 | 31.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 200,000 | 9 | 44.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 200,000 | 5 | 34.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 500,000 | 9 | 42.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 500,000 | 5 | 42.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe780-il | 1,000,000 | 9 | 50.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe780-il | 1,000,000 | 5 | 44 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
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