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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(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 |
(goe553-il) GOE 553 AIRFOIL | Gottingen 553 airfoil Max thickness 13.7% at 29.6% chord Max camber 4.7% at 39.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe54-il,goe553-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| goe553-il | 50,000 | 9 | 11.2 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 50,000 | 5 | 30.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 100,000 | 9 | 45.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 100,000 | 5 | 54.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 200,000 | 9 | 73 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 200,000 | 5 | 75 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 500,000 | 9 | 105.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 500,000 | 5 | 102.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe553-il | 1,000,000 | 9 | 130.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe553-il | 1,000,000 | 5 | 122.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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