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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(ag09-il) AG09 | Drela AG09 airfoil Max thickness 4.9% at 17.4% chord Max camber 1.8% at 34.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag09-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag09-il | 50,000 | 9 | 32.4 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag09-il | 50,000 | 5 | 32.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag09-il | 100,000 | 9 | 44.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag09-il | 100,000 | 5 | 44.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag09-il | 200,000 | 9 | 56.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag09-il | 200,000 | 5 | 55.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag09-il | 500,000 | 9 | 74.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag09-il | 500,000 | 5 | 70.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag09-il | 1,000,000 | 9 | 87 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag09-il | 1,000,000 | 5 | 82 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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