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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(ag35-il) AG35 | Drela AG35 airfoil Max thickness 8.7% at 27.9% chord Max camber 2.3% at 37% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag35-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag35-il | 50,000 | 9 | 32.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag35-il | 50,000 | 5 | 36.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag35-il | 100,000 | 9 | 50.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag35-il | 100,000 | 5 | 51.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag35-il | 200,000 | 9 | 68.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag35-il | 200,000 | 5 | 65.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag35-il | 500,000 | 9 | 90.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag35-il | 500,000 | 5 | 82.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag35-il | 1,000,000 | 9 | 105.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag35-il | 1,000,000 | 5 | 95.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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