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 | ||
(sc20012-il) NASA SC(2)-0012 AIRFOIL | NASA SC(2)-0012 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (sc20012-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20012-il | 50,000 | 9 | 24.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 50,000 | 5 | 23.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 100,000 | 9 | 33.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 100,000 | 5 | 29.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 200,000 | 9 | 36 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 200,000 | 5 | 39.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 500,000 | 9 | 53.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 500,000 | 5 | 58.6 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20012-il | 1,000,000 | 9 | 71.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20012-il | 1,000,000 | 5 | 72.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||