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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(ag17-il) AG17 | Drela AG17 airfoil Max thickness 6.5% at 22.1% chord Max camber 2% at 45.5% chord | Remove Airfoil details Airfoil plotter |
(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 |
(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 |
(ag08-il) AG08 | Drela AG08 airfoil Max thickness 5.8% at 21% chord Max camber 1.7% at 40.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag17-il,ag11-il,ag09-il,ag08-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag17-il | 50,000 | 9 | 34.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag17-il | 50,000 | 5 | 36.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag17-il | 100,000 | 9 | 49.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag17-il | 100,000 | 5 | 48.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag17-il | 200,000 | 9 | 64.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag17-il | 200,000 | 5 | 60.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag17-il | 500,000 | 9 | 82.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag17-il | 500,000 | 5 | 76.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag17-il | 1,000,000 | 9 | 95.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag17-il | 1,000,000 | 5 | 89.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| 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 | |
| ag08-il | 50,000 | 9 | 32.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 50,000 | 5 | 33.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 100,000 | 9 | 45.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 100,000 | 5 | 45.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 200,000 | 9 | 58.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 200,000 | 5 | 56.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 500,000 | 9 | 76.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 500,000 | 5 | 72 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 1,000,000 | 9 | 89 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 1,000,000 | 5 | 83.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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