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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(ag14-il) AG14 | Drela AG14 airfoil Max thickness 5.4% at 19.9% chord Max camber 2% at 41.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag14-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag14-il | 50,000 | 9 | 34.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 50,000 | 5 | 35.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 100,000 | 9 | 48.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 100,000 | 5 | 47.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 200,000 | 9 | 62.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 200,000 | 5 | 59.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 500,000 | 9 | 80.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 500,000 | 5 | 76 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 1,000,000 | 9 | 93.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 1,000,000 | 5 | 89.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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