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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(eh3012-il) EH 3.0/12 | John Yost EH 3.0/12 for tailless R/C aircraft Max thickness 12% at 30% chord Max camber 2.9% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (eh3012-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| eh3012-il | 50,000 | 9 | 14.6 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh3012-il | 50,000 | 5 | 26 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh3012-il | 100,000 | 9 | 39.6 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh3012-il | 100,000 | 5 | 46.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh3012-il | 200,000 | 9 | 64.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh3012-il | 200,000 | 5 | 65.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh3012-il | 500,000 | 9 | 93.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh3012-il | 500,000 | 5 | 77.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh3012-il | 1,000,000 | 9 | 107.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh3012-il | 1,000,000 | 5 | 74.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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