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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(ag11-il) AG11 | Drela AG11 airfoil Max thickness 5.8% at 26% chord Max camber 2.2% at 29.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag11-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag11-il | 50,000 | 9 | 33 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag11-il | 50,000 | 5 | 34.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag11-il | 100,000 | 9 | 46.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag11-il | 100,000 | 5 | 46.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag11-il | 200,000 | 9 | 59.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag11-il | 200,000 | 5 | 58.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag11-il | 500,000 | 9 | 77.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag11-il | 500,000 | 5 | 75.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag11-il | 1,000,000 | 9 | 91.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag11-il | 1,000,000 | 5 | 91 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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