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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(eh2012-il) EH 2.0/12 | John Yost EH 2.0/12 for tailless R/C aircraft Max thickness 12% at 28.7% chord Max camber 2% at 25.9% chord | Remove Airfoil details Airfoil plotter |
(ag45c03-il) AG45c -03f | Drela AG45c -03f airfoil Max thickness 6.9% at 23.5% chord Max camber 2% at 31.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (eh2012-il,ag45c03-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| eh2012-il | 50,000 | 9 | 18 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2012-il | 50,000 | 5 | 28.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2012-il | 100,000 | 9 | 42.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2012-il | 100,000 | 5 | 45.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2012-il | 200,000 | 9 | 61.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2012-il | 200,000 | 5 | 63.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2012-il | 500,000 | 9 | 89.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2012-il | 500,000 | 5 | 85.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2012-il | 1,000,000 | 9 | 106.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2012-il | 1,000,000 | 5 | 97.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45c03-il | 50,000 | 9 | 29.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45c03-il | 50,000 | 5 | 34.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45c03-il | 100,000 | 9 | 46 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45c03-il | 100,000 | 5 | 47.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45c03-il | 200,000 | 9 | 62.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45c03-il | 200,000 | 5 | 61 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45c03-il | 500,000 | 9 | 83 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45c03-il | 500,000 | 5 | 78.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45c03-il | 1,000,000 | 9 | 97.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45c03-il | 1,000,000 | 5 | 91.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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