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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(goe648-il) GOE 648 AIRFOIL | Gottingen 648 airfoil Max thickness 15.2% at 29.4% chord Max camber 3.9% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(goe803h-il) GOE 803 (HACKLINGER) AIRFOIL | Gottingen 803 (Hacklinger) airfoil Max thickness 6.3% at 15% chord Max camber 6.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe54-il) GOE 54 AIRFOIL | Gottingen 54 airfoil Max thickness 6.5% at 14.9% chord Max camber 3.5% at 19.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe648-il,goe803h-il,goe54-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe648-il | 50,000 | 9 | 22.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 50,000 | 5 | 30.5 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 100,000 | 9 | 43.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 100,000 | 5 | 44.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 200,000 | 9 | 57.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 200,000 | 5 | 57.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 500,000 | 9 | 79.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 500,000 | 5 | 80.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe648-il | 1,000,000 | 9 | 104.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe648-il | 1,000,000 | 5 | 101.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe803h-il | 50,000 | 9 | 40 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe803h-il | 50,000 | 5 | 48.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe803h-il | 100,000 | 9 | 69.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe803h-il | 100,000 | 5 | 69.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe803h-il | 200,000 | 9 | 95.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe803h-il | 200,000 | 5 | 85.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe803h-il | 500,000 | 9 | 112.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe803h-il | 500,000 | 5 | 103.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe803h-il | 1,000,000 | 9 | 128.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe803h-il | 1,000,000 | 5 | 122.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe54-il | 50,000 | 9 | 19.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe54-il | 50,000 | 5 | 29.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe54-il | 100,000 | 9 | 34.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe54-il | 100,000 | 5 | 44.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe54-il | 200,000 | 9 | 58.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe54-il | 200,000 | 5 | 64.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe54-il | 500,000 | 9 | 87.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe54-il | 500,000 | 5 | 88.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe54-il | 1,000,000 | 9 | 106.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe54-il | 1,000,000 | 5 | 105.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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