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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(ag10-il) AG10 | Drela AG10 airfoil Max thickness 4.7% at 16% chord Max camber 1.7% at 32.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag10-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag10-il | 50,000 | 9 | 31.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 50,000 | 5 | 31 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 100,000 | 9 | 41.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 100,000 | 5 | 41.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 200,000 | 9 | 52.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 200,000 | 5 | 52.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 500,000 | 9 | 69.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 500,000 | 5 | 67.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag10-il | 1,000,000 | 9 | 81.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag10-il | 1,000,000 | 5 | 79.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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