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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(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 |
(goe795-il) GOE 795 AIRFOIL | Gottingen 795 airfoil Max thickness 8% at 30.9% chord Max camber 2.4% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(goe654-il) GOE 654 AIRFOIL | Gottingen 654 airfoil Max thickness 14.5% at 30% chord Max camber 5.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe645-il) GOE 645 AIRFOIL | Gottingen 645 airfoil Max thickness 15.4% at 19.4% chord Max camber 4.8% at 39.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe798-il,goe795-il,goe654-il,goe645-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| goe795-il | 50,000 | 9 | 38 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe795-il | 50,000 | 5 | 37.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe795-il | 100,000 | 9 | 56.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe795-il | 100,000 | 5 | 53.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe795-il | 200,000 | 9 | 75.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe795-il | 200,000 | 5 | 67.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe795-il | 500,000 | 9 | 95.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe795-il | 500,000 | 5 | 80.2 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe795-il | 1,000,000 | 9 | 105 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe795-il | 1,000,000 | 5 | 84.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe654-il | 50,000 | 9 | 10 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe654-il | 50,000 | 5 | 28.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe654-il | 100,000 | 9 | 41 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe654-il | 100,000 | 5 | 50 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe654-il | 200,000 | 9 | 67.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe654-il | 200,000 | 5 | 67.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe654-il | 500,000 | 9 | 94.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe654-il | 500,000 | 5 | 92.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe654-il | 1,000,000 | 9 | 118.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe654-il | 1,000,000 | 5 | 115.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 50,000 | 9 | 9.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 50,000 | 5 | 28.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 100,000 | 9 | 43.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 100,000 | 5 | 48.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 200,000 | 9 | 66.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 200,000 | 5 | 65.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 500,000 | 9 | 93.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 500,000 | 5 | 84.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe645-il | 1,000,000 | 9 | 110.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe645-il | 1,000,000 | 5 | 88.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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