Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(ag44ct02r-il) AG44ct -02f | Drela AG44ct -02f airfoil Max thickness 7.3% at 24.6% chord Max camber 1.9% at 34.4% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (ag44ct02r-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag44ct02r-il | 50,000 | 9 | 30.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 50,000 | 5 | 34.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 100,000 | 9 | 45.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 100,000 | 5 | 47.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 200,000 | 9 | 61.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 200,000 | 5 | 60.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 500,000 | 9 | 82.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 500,000 | 5 | 78.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag44ct02r-il | 1,000,000 | 9 | 97.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag44ct02r-il | 1,000,000 | 5 | 91.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||