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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(goe499-il) GOE 499 AIRFOIL | Gottingen 499 airfoil Max thickness 6.8% at 30% chord Max camber 5.9% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe364-il) GOE 364 AIRFOIL | Gottingen 364 airfoil Max thickness 10.8% at 30% chord Max camber 6.5% at 30% chord | Remove Airfoil details Airfoil plotter |
(e1233-il) EPPLER 1233 AIRFOIL | Eppler E1233 general aviation airfoil Max thickness 18.9% at 29.8% chord Max camber 4.4% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(goe450-il) GOE 450 AIRFOIL | Gottingen 450 airfoil Max thickness 8.9% at 29.9% chord Max camber 5.2% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe118-il) GOE 118 (MVA MK.7) AIRFOIL | Gottingen 118 (MVA MK.7) airfoil Max thickness 8.6% at 29.9% chord Max camber 5.7% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe499-il,goe364-il,e1233-il,goe450-il,goe118-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe499-il | 50,000 | 9 | 38.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 50,000 | 5 | 44.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 100,000 | 9 | 71.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 100,000 | 5 | 69.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 200,000 | 9 | 102.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 200,000 | 5 | 99.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 500,000 | 9 | 149.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 500,000 | 5 | 118.3 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe499-il | 1,000,000 | 9 | 157.8 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe499-il | 1,000,000 | 5 | 111.9 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe364-il | 50,000 | 9 | 13.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe364-il | 50,000 | 5 | 34.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe364-il | 100,000 | 9 | 52.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe364-il | 100,000 | 5 | 57 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe364-il | 200,000 | 9 | 76.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe364-il | 200,000 | 5 | 76.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe364-il | 500,000 | 9 | 107.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe364-il | 500,000 | 5 | 104 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe364-il | 1,000,000 | 9 | 133.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe364-il | 1,000,000 | 5 | 124.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 50,000 | 9 | 15.7 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 50,000 | 5 | 21.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 100,000 | 9 | 34 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 100,000 | 5 | 41.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 200,000 | 9 | 56.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 200,000 | 5 | 58.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 500,000 | 9 | 81 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 500,000 | 5 | 81.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 1,000,000 | 9 | 104.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 1,000,000 | 5 | 103.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe450-il | 50,000 | 9 | 39.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe450-il | 50,000 | 5 | 40.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe450-il | 100,000 | 9 | 63.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe450-il | 100,000 | 5 | 64.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe450-il | 200,000 | 9 | 88.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe450-il | 200,000 | 5 | 85.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe450-il | 500,000 | 9 | 120.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe450-il | 500,000 | 5 | 108 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe450-il | 1,000,000 | 9 | 141.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe450-il | 1,000,000 | 5 | 118.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe118-il | 50,000 | 9 | 24.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe118-il | 50,000 | 5 | 40.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe118-il | 100,000 | 9 | 62 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe118-il | 100,000 | 5 | 61.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe118-il | 200,000 | 9 | 83.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe118-il | 200,000 | 5 | 82.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe118-il | 500,000 | 9 | 112.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe118-il | 500,000 | 5 | 108.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe118-il | 1,000,000 | 9 | 134.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe118-il | 1,000,000 | 5 | 120.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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