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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(goe279-il) GOE 279 (DAIMLER X) AIRFOIL | Gottingen 279 (DAIMLER X) airfoil Max thickness 7.4% at 30% chord Max camber 4.7% at 40% chord | Remove Airfoil details Airfoil plotter |
(eiffel371-il) Eiffel 371 (Monge) | Eiffel 371 (Monge) airfoil Max thickness 14.4% at 30% chord Max camber 3.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe437-il) GOE 437 AIRFOIL | Gottingen 437 airfoil Max thickness 7.1% at 30% chord Max camber 4.8% at 40% chord | Remove Airfoil details Airfoil plotter |
(e398-il) EPPLER 398 AIRFOIL | Eppler E398 human powered aircraft airfoil Max thickness 14.2% at 29.6% chord Max camber 5.3% at 50.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe279-il,eiffel371-il,goe437-il,e398-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe279-il | 50,000 | 9 | 37.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe279-il | 50,000 | 5 | 42.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe279-il | 100,000 | 9 | 58.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe279-il | 100,000 | 5 | 59 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe279-il | 200,000 | 9 | 77.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe279-il | 200,000 | 5 | 73.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe279-il | 500,000 | 9 | 96.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe279-il | 500,000 | 5 | 93 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe279-il | 1,000,000 | 9 | 113.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe279-il | 1,000,000 | 5 | 105 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel371-il | 50,000 | 9 | 19.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel371-il | 50,000 | 5 | 31.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel371-il | 100,000 | 9 | 47.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel371-il | 100,000 | 5 | 42.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel371-il | 200,000 | 9 | 56.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel371-il | 200,000 | 5 | 52 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel371-il | 500,000 | 9 | 70.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel371-il | 500,000 | 5 | 69.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eiffel371-il | 1,000,000 | 9 | 89.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eiffel371-il | 1,000,000 | 5 | 80.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe437-il | 50,000 | 9 | 41.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe437-il | 50,000 | 5 | 42.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe437-il | 100,000 | 9 | 59.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe437-il | 100,000 | 5 | 60.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe437-il | 200,000 | 9 | 78.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe437-il | 200,000 | 5 | 80 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe437-il | 500,000 | 9 | 106.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe437-il | 500,000 | 5 | 105.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe437-il | 1,000,000 | 9 | 128.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe437-il | 1,000,000 | 5 | 123.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 50,000 | 9 | 6.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 50,000 | 5 | 17.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 100,000 | 9 | 47.5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 100,000 | 5 | 54.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 200,000 | 9 | 84.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 200,000 | 5 | 86.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 500,000 | 9 | 129 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 500,000 | 5 | 124.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e398-il | 1,000,000 | 9 | 163.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e398-il | 1,000,000 | 5 | 147 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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