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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(goe420-il) GOE 420 AIRFOIL | Gottingen 420 airfoil Max thickness 18.8% at 30% chord Max camber 4.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe423-il) GOE 423 AIRFOIL | Gottingen 423 airfoil Max thickness 16.9% at 39.7% chord Max camber 5.1% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe420-il,goe423-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe420-il | 50,000 | 9 | 4 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 50,000 | 5 | 13.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 100,000 | 9 | 32.7 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 100,000 | 5 | 44.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 200,000 | 9 | 66.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 200,000 | 5 | 62.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 500,000 | 9 | 89.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 500,000 | 5 | 83.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 1,000,000 | 9 | 111.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 1,000,000 | 5 | 102.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 50,000 | 9 | 4.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 50,000 | 5 | 14.4 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 100,000 | 9 | 22.8 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 100,000 | 5 | 40.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 200,000 | 9 | 69.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 200,000 | 5 | 70.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 500,000 | 9 | 105.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 500,000 | 5 | 101.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe423-il | 1,000,000 | 9 | 133.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe423-il | 1,000,000 | 5 | 124.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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