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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(goe314-il) GOE 314 (HANSA-BRANDENBURG) AIRFOIL | Gottingen 314 (Hansa-Brandenburg) airfoil Max thickness 8% at 29.9% chord Max camber 4.7% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(goe525-il) GOE 525 AIRFOIL | Gottingen 525 airfoil Max thickness 16.5% at 29.7% chord Max camber 9.7% at 49.7% chord | Remove Airfoil details Airfoil plotter |
(goe602-il) GOE 602 AIRFOIL | Gottingen 602 airfoil Max thickness 10% at 30% chord Max camber 3.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe314-il,goe525-il,goe602-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe314-il | 50,000 | 9 | 28.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe314-il | 50,000 | 5 | 36.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe314-il | 100,000 | 9 | 48.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe314-il | 100,000 | 5 | 54.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe314-il | 200,000 | 9 | 70.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe314-il | 200,000 | 5 | 71.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe314-il | 500,000 | 9 | 98.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe314-il | 500,000 | 5 | 91 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe314-il | 1,000,000 | 9 | 117.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe314-il | 1,000,000 | 5 | 104.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe525-il | 50,000 | 9 | 5.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe525-il | 50,000 | 5 | 20.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe525-il | 100,000 | 9 | 48.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe525-il | 100,000 | 5 | 50.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe525-il | 200,000 | 9 | 74.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe525-il | 200,000 | 5 | 71.5 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe525-il | 500,000 | 9 | 102.1 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe525-il | 500,000 | 5 | 90.6 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe525-il | 1,000,000 | 9 | 120.6 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe525-il | 1,000,000 | 5 | 104.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602-il | 50,000 | 9 | 37.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602-il | 50,000 | 5 | 39.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602-il | 100,000 | 9 | 57.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602-il | 100,000 | 5 | 57.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602-il | 200,000 | 9 | 77.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602-il | 200,000 | 5 | 74 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602-il | 500,000 | 9 | 102.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602-il | 500,000 | 5 | 93.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe602-il | 1,000,000 | 9 | 119.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe602-il | 1,000,000 | 5 | 104.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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