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 | ||
(e224-il) E224 (10.17%) | Eppler E224 low Reynolds number airfoil Max thickness 10.2% at 29.8% chord Max camber 1.5% at 54.2% chord | Remove Airfoil details Airfoil plotter |
(c141e-il) LOCKHEED C-141 BL761.11 AIRFOIL | Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.5% at 40.2% chord Max camber 1.8% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e224-il,c141e-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e224-il | 50,000 | 9 | 33.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 50,000 | 5 | 35.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 100,000 | 9 | 51.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 100,000 | 5 | 50.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 200,000 | 9 | 68.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 200,000 | 5 | 63.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 500,000 | 9 | 89.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 500,000 | 5 | 79.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e224-il | 1,000,000 | 9 | 102.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e224-il | 1,000,000 | 5 | 88.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 50,000 | 9 | 33.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 50,000 | 5 | 31.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 100,000 | 9 | 49.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 100,000 | 5 | 45.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 200,000 | 9 | 69.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 200,000 | 5 | 59.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 500,000 | 9 | 88.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 500,000 | 5 | 65.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c141e-il | 1,000,000 | 9 | 88.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c141e-il | 1,000,000 | 5 | 78.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||