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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(goe620-il) GOE 620 AIRFOIL | Gottingen 620 airfoil Max thickness 17.5% at 30% chord Max camber 5.9% at 50% chord | Remove Airfoil details Airfoil plotter |
(goe342-il) GOE 342 AIRFOIL | Gottingen 342 airfoil Max thickness 5.4% at 20% chord Max camber 6.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(e344-il) EPPLER 344 AIRFOIL | Eppler E344 flying wing airfoil Max thickness 14.7% at 29.9% chord Max camber 4.3% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe620-il,goe342-il,e344-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe620-il | 50,000 | 9 | 4.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 50,000 | 5 | 14.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 100,000 | 9 | 42.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 100,000 | 5 | 43.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 200,000 | 9 | 71.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 200,000 | 5 | 64.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 500,000 | 9 | 97.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 500,000 | 5 | 82.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe620-il | 1,000,000 | 9 | 117.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe620-il | 1,000,000 | 5 | 87.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 50,000 | 9 | 44.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 50,000 | 5 | 47.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 100,000 | 9 | 71.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 100,000 | 5 | 71.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 200,000 | 9 | 99.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 200,000 | 5 | 85.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 500,000 | 9 | 109.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 500,000 | 5 | 105.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 1,000,000 | 9 | 130.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 1,000,000 | 5 | 111.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 50,000 | 9 | 14.3 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 50,000 | 5 | 24.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 100,000 | 9 | 31.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 100,000 | 5 | 44 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 200,000 | 9 | 58 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 200,000 | 5 | 65.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 500,000 | 9 | 94.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 500,000 | 5 | 91.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e344-il | 1,000,000 | 9 | 118.8 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e344-il | 1,000,000 | 5 | 116.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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