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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(ag45ct02r-il) AG45ct -02f | Drela AG45ct -02f airfoil Max thickness 6.9% at 23.3% chord Max camber 1.8% at 33.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag45ct02r-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag45ct02r-il | 50,000 | 9 | 30.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 50,000 | 5 | 34.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 100,000 | 9 | 45.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 100,000 | 5 | 46.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 200,000 | 9 | 60.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 200,000 | 5 | 59.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 500,000 | 9 | 80.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 500,000 | 5 | 76.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 1,000,000 | 9 | 94.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 1,000,000 | 5 | 89.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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