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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(goe281-il) GOE 281 (DAIMLER XII) AIRFOIL | Gottingen 281 (DAIMLER XII) airfoil Max thickness 8% at 30% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe100-il) GOE 100 (SOPWITH) AIRFOIL | Gottingen 100 (Sopwith) airfoil Max thickness 6.6% at 20% chord Max camber 3.6% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe29b-il) GOE 29B AIRFOIL | Gottingen 29B airfoil Max thickness 9.4% at 19.8% chord Max camber 6.5% at 29.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe281-il,goe100-il,goe29b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe281-il | 50,000 | 9 | 36.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe281-il | 50,000 | 5 | 42.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe281-il | 100,000 | 9 | 59 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe281-il | 100,000 | 5 | 59.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe281-il | 200,000 | 9 | 79.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe281-il | 200,000 | 5 | 75.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe281-il | 500,000 | 9 | 101.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe281-il | 500,000 | 5 | 95.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe281-il | 1,000,000 | 9 | 118.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe281-il | 1,000,000 | 5 | 98.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 50,000 | 9 | 37.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 50,000 | 5 | 38 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 100,000 | 9 | 54.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 100,000 | 5 | 50.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 200,000 | 9 | 71.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 200,000 | 5 | 61.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 500,000 | 9 | 88.2 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 500,000 | 5 | 73.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe100-il | 1,000,000 | 9 | 88.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe100-il | 1,000,000 | 5 | 83.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe29b-il | 50,000 | 9 | 22.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe29b-il | 50,000 | 5 | 37.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe29b-il | 100,000 | 9 | 52.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe29b-il | 100,000 | 5 | 57.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe29b-il | 200,000 | 9 | 77.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe29b-il | 200,000 | 5 | 75 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe29b-il | 500,000 | 9 | 99.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe29b-il | 500,000 | 5 | 94.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe29b-il | 1,000,000 | 9 | 118.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe29b-il | 1,000,000 | 5 | 116.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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