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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(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 |
(eh0009-il) EH 0.0/9.0 | John Yost EH 0.0/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ea61009-il,eh0009-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| eh0009-il | 50,000 | 9 | 26.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh0009-il | 50,000 | 5 | 26.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh0009-il | 100,000 | 9 | 37.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh0009-il | 100,000 | 5 | 35.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh0009-il | 200,000 | 9 | 47.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh0009-il | 200,000 | 5 | 43.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh0009-il | 500,000 | 9 | 59.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh0009-il | 500,000 | 5 | 55 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh0009-il | 1,000,000 | 9 | 66.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh0009-il | 1,000,000 | 5 | 67.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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