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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(ag47ct02r-il) AG47ct -02f rot. | Drela AG47ct -02f airfoil Max thickness 5% at 22.5% chord Max camber 1.2% at 33.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag47ct02r-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag47ct02r-il | 50,000 | 9 | 30.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 50,000 | 5 | 30.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 100,000 | 9 | 41.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 100,000 | 5 | 38.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 200,000 | 9 | 52.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 200,000 | 5 | 49.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 500,000 | 9 | 65.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 500,000 | 5 | 66.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag47ct02r-il | 1,000,000 | 9 | 80.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag47ct02r-il | 1,000,000 | 5 | 80.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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