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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(goe210-il) GOE 210 (DAIMLER) AIRFOIL | Gottingen 210 (DAIMLER) airfoil Max thickness 6.6% at 30% chord Max camber 4.3% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe184-il) GOE 184 (MVA H.29) AIRFOIL | Gottingen 184 (MVA H.29) airfoil Max thickness 8.3% at 19.9% chord Max camber 5.3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe210-il,goe184-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe210-il | 50,000 | 9 | 40.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 50,000 | 5 | 43.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 100,000 | 9 | 62 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 100,000 | 5 | 62 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 200,000 | 9 | 82.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 200,000 | 5 | 77.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 500,000 | 9 | 105.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 500,000 | 5 | 86.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe210-il | 1,000,000 | 9 | 116.7 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe210-il | 1,000,000 | 5 | 99.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 50,000 | 9 | 34 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 50,000 | 5 | 39.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 100,000 | 9 | 57.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 100,000 | 5 | 60.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 200,000 | 9 | 79.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 200,000 | 5 | 79.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 500,000 | 9 | 107.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 500,000 | 5 | 102.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe184-il | 1,000,000 | 9 | 127.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe184-il | 1,000,000 | 5 | 111.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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