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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(goe584-il) GOE 584 AIRFOIL | Gottingen 584 airfoil Max thickness 12.7% at 30% chord Max camber 5% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe630-il) GOE 630 AIRFOIL | Gottingen 630 airfoil Max thickness 12.6% at 29.8% chord Max camber 7.7% at 39.8% chord | Remove Airfoil details Airfoil plotter |
(goe590-il) GOE 590 AIRFOIL | Gottingen 590 airfoil Max thickness 5.7% at 30% chord Max camber 4% at 30% 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 (goe584-il,goe630-il,goe590-il,goe553-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe584-il | 50,000 | 9 | 8.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 50,000 | 5 | 26 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 100,000 | 9 | 51.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 100,000 | 5 | 55 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 200,000 | 9 | 78.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 200,000 | 5 | 77.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 500,000 | 9 | 112.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 500,000 | 5 | 106 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe584-il | 1,000,000 | 9 | 137.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe584-il | 1,000,000 | 5 | 126.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 50,000 | 9 | 7.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 50,000 | 5 | 28.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 100,000 | 9 | 48.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 100,000 | 5 | 54.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 200,000 | 9 | 74.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 200,000 | 5 | 73.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 500,000 | 9 | 103.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 500,000 | 5 | 99.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe630-il | 1,000,000 | 9 | 129 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe630-il | 1,000,000 | 5 | 123.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe590-il | 50,000 | 9 | 37.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe590-il | 50,000 | 5 | 38.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe590-il | 100,000 | 9 | 52.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe590-il | 100,000 | 5 | 53.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe590-il | 200,000 | 9 | 67.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe590-il | 200,000 | 5 | 70.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe590-il | 500,000 | 9 | 94.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe590-il | 500,000 | 5 | 93.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe590-il | 1,000,000 | 9 | 114.6 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe590-il | 1,000,000 | 5 | 111.5 at α=3.75° | 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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