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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(goe500-il) GOE 500 AIRFOIL | Gottingen 500 airfoil Max thickness 10% at 30% chord Max camber 6% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe502-il) GOE 502 AIRFOIL | Gottingen 502 airfoil Max thickness 15.9% at 29.3% chord Max camber 6.1% at 49.4% chord | Remove Airfoil details Airfoil plotter |
(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 |
(goe510-il) GOE 510 AIRFOIL | Gottingen 510 airfoil Max thickness 13.7% at 19.7% chord Max camber 5.8% at 39.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe500-il,goe502-il,goe499-il,goe510-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe500-il | 50,000 | 9 | 35.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 50,000 | 5 | 36.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 100,000 | 9 | 64.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 100,000 | 5 | 65.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 200,000 | 9 | 92 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 200,000 | 5 | 91.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 500,000 | 9 | 131.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 500,000 | 5 | 120.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe500-il | 1,000,000 | 9 | 159.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe500-il | 1,000,000 | 5 | 120.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 50,000 | 9 | 5.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 50,000 | 5 | 18.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 100,000 | 9 | 42.1 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 100,000 | 5 | 53 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 200,000 | 9 | 76 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 200,000 | 5 | 75.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 500,000 | 9 | 106.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 500,000 | 5 | 100.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe502-il | 1,000,000 | 9 | 132.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe502-il | 1,000,000 | 5 | 112.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| goe510-il | 50,000 | 9 | 8.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 50,000 | 5 | 29.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 100,000 | 9 | 48.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 100,000 | 5 | 48.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 200,000 | 9 | 65.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 200,000 | 5 | 61.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 500,000 | 9 | 84.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 500,000 | 5 | 82.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe510-il | 1,000,000 | 9 | 106.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe510-il | 1,000,000 | 5 | 99.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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