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 | ||
(a18sm-il) A18 (smoothed) | Archer A18 F1C free flight airfoil (smoothed) Max thickness 7.3% at 27.1% chord Max camber 3.8% at 49.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (a18sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| a18sm-il | 50,000 | 9 | 44.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 50,000 | 5 | 44.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 100,000 | 9 | 65.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 100,000 | 5 | 63.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 200,000 | 9 | 87 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 200,000 | 5 | 81.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 500,000 | 9 | 114.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 500,000 | 5 | 102.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| a18sm-il | 1,000,000 | 9 | 132.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| a18sm-il | 1,000,000 | 5 | 116 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||