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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(goe604-il) GOE 604 AIRFOIL | Gottingen 604 airfoil Max thickness 17.8% at 29.3% chord Max camber 5.4% at 29.3% chord | Remove Airfoil details Airfoil plotter |
(ea61009-il) EPPLER EA 6(-1)-009 AIRFOIL | Eppler EA 6(-1)-009 airfoil Max thickness 9% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(vr14-il) BOEING-VERTOL VR-14 AIRFOIL | Boeing-Vertol/Dadone VR-14 rotorcraft airfoil Max thickness 8% at 35% chord Max camber 1.7% at 20% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe604-il,ea61009-il,vr14-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe604-il | 50,000 | 9 | 3.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 50,000 | 5 | 20.6 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 100,000 | 9 | 29.8 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 100,000 | 5 | 42.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 200,000 | 9 | 59.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 200,000 | 5 | 61.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 500,000 | 9 | 87.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 500,000 | 5 | 85.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe604-il | 1,000,000 | 9 | 113 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe604-il | 1,000,000 | 5 | 108.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ea61009-il | 50,000 | 9 | 23.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ea61009-il | 50,000 | 5 | 21.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ea61009-il | 100,000 | 9 | 29.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ea61009-il | 100,000 | 5 | 27.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ea61009-il | 200,000 | 9 | 31.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ea61009-il | 200,000 | 5 | 33.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ea61009-il | 500,000 | 9 | 46.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ea61009-il | 500,000 | 5 | 58.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ea61009-il | 1,000,000 | 9 | 72.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ea61009-il | 1,000,000 | 5 | 76 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr14-il | 50,000 | 9 | 29.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr14-il | 50,000 | 5 | 29 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr14-il | 100,000 | 9 | 40.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr14-il | 100,000 | 5 | 40.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr14-il | 200,000 | 9 | 50.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr14-il | 200,000 | 5 | 54.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr14-il | 500,000 | 9 | 74.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr14-il | 500,000 | 5 | 73.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr14-il | 1,000,000 | 9 | 91.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr14-il | 1,000,000 | 5 | 87.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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