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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(eh2010-il) EH 2.0/10 | John Yost EH 2.0/10 for tailless R/C aircraft Max thickness 10.1% at 28.7% chord Max camber 2% at 25.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (eh2010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| eh2010-il | 50,000 | 9 | 19.7 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2010-il | 50,000 | 5 | 30.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2010-il | 100,000 | 9 | 46.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2010-il | 100,000 | 5 | 47.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2010-il | 200,000 | 9 | 63.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2010-il | 200,000 | 5 | 63 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2010-il | 500,000 | 9 | 87.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2010-il | 500,000 | 5 | 83.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2010-il | 1,000,000 | 9 | 106.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2010-il | 1,000,000 | 5 | 94.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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