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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(eh2070-il) EH 2.0/7.0 | John Yost EH 2.0/7.0 for tailless R/C aircraft Max thickness 7% at 28.7% chord Max camber 2% at 25.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (eh2070-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| eh2070-il | 50,000 | 9 | 33.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2070-il | 50,000 | 5 | 33.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2070-il | 100,000 | 9 | 46.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2070-il | 100,000 | 5 | 45.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2070-il | 200,000 | 9 | 60 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2070-il | 200,000 | 5 | 58.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2070-il | 500,000 | 9 | 79.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2070-il | 500,000 | 5 | 75.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2070-il | 1,000,000 | 9 | 94.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2070-il | 1,000,000 | 5 | 86.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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