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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(goe494-il) GOE 494 AIRFOIL | Gottingen 494 airfoil Max thickness 5% at 20% chord Max camber 5.1% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe318-il) GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL | Gottingen 318 (Hansa-Brandenburg VI.5) airfoil Max thickness 9.1% at 29.9% chord Max camber 4.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(goe358-il) GOE 358 AIRFOIL | Gottingen 358 airfoil Max thickness 10.9% at 20% chord Max camber 5.6% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe494-il,goe318-il,goe358-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe494-il | 50,000 | 9 | 44.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 50,000 | 5 | 45.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 100,000 | 9 | 69.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 100,000 | 5 | 69.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 200,000 | 9 | 97 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 200,000 | 5 | 95.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 500,000 | 9 | 135.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 500,000 | 5 | 121.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe494-il | 1,000,000 | 9 | 164.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe494-il | 1,000,000 | 5 | 112.3 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe318-il | 50,000 | 9 | 20.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe318-il | 50,000 | 5 | 35.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe318-il | 100,000 | 9 | 50.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe318-il | 100,000 | 5 | 53.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe318-il | 200,000 | 9 | 69 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe318-il | 200,000 | 5 | 70 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe318-il | 500,000 | 9 | 93.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe318-il | 500,000 | 5 | 92.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe318-il | 1,000,000 | 9 | 113.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe318-il | 1,000,000 | 5 | 111 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 50,000 | 9 | 37.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 50,000 | 5 | 42.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 100,000 | 9 | 58.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 100,000 | 5 | 61.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 200,000 | 9 | 79 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 200,000 | 5 | 79 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 500,000 | 9 | 105.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 500,000 | 5 | 99.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe358-il | 1,000,000 | 9 | 119.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe358-il | 1,000,000 | 5 | 115.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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