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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(eh1090-il) EH 1.0/9.0 | John Yost EH 1.0/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 1% at 25.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (eh1090-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| eh1090-il | 50,000 | 9 | 29.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1090-il | 50,000 | 5 | 31.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1090-il | 100,000 | 9 | 43.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1090-il | 100,000 | 5 | 43 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1090-il | 200,000 | 9 | 56.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1090-il | 200,000 | 5 | 54.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1090-il | 500,000 | 9 | 74.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1090-il | 500,000 | 5 | 68.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh1090-il | 1,000,000 | 9 | 84.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh1090-il | 1,000,000 | 5 | 73.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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