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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(goe440-il) GOE 440 AIRFOIL | Gottingen 440 airfoil Max thickness 15.3% at 30% chord Max camber 9.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe393-il) GOE 393 AIRFOIL | Gottingen 393 airfoil Max thickness 6.1% at 19.9% chord Max camber 4.2% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(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 |
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Polars for (goe440-il,goe393-il,goe420-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe440-il | 50,000 | 9 | 9.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 50,000 | 5 | 31.9 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 100,000 | 9 | 53.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 100,000 | 5 | 52.9 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 200,000 | 9 | 71.1 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 200,000 | 5 | 67.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 500,000 | 9 | 92.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 500,000 | 5 | 86.7 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe440-il | 1,000,000 | 9 | 109.5 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe440-il | 1,000,000 | 5 | 100.3 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe393-il | 50,000 | 9 | 34.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe393-il | 50,000 | 5 | 39.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe393-il | 100,000 | 9 | 55.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe393-il | 100,000 | 5 | 57.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe393-il | 200,000 | 9 | 75.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe393-il | 200,000 | 5 | 74.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe393-il | 500,000 | 9 | 101.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe393-il | 500,000 | 5 | 97.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe393-il | 1,000,000 | 9 | 120.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe393-il | 1,000,000 | 5 | 113.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
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