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 | ||
(sc21010-il) NASA SC(2)-1010 AIRFOIL | NASA SC(2)-1010 airfoil Max thickness 10% at 32% chord Max camber 2.8% at 71% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (sc21010-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc21010-il | 50,000 | 9 | 32.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21010-il | 50,000 | 5 | 36.1 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21010-il | 100,000 | 9 | 48.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21010-il | 100,000 | 5 | 49.6 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21010-il | 200,000 | 9 | 69.3 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21010-il | 200,000 | 5 | 67.7 at α=-0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21010-il | 500,000 | 9 | 100.8 at α=-0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21010-il | 500,000 | 5 | 85.6 at α=-1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc21010-il | 1,000,000 | 9 | 115.3 at α=-1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc21010-il | 1,000,000 | 5 | 89.9 at α=-2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||