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 | ||
(rc1064c-il) NASA/LANGLEY RC10-64C AIRFOIL | NASA/Langley 10-64C rotorcraft airfoil Max thickness 10% at 40% chord Max camber 1% at 35% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (rc1064c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rc1064c-il | 50,000 | 9 | 31.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 50,000 | 5 | 30.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 100,000 | 9 | 45.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 100,000 | 5 | 41.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 200,000 | 9 | 57.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 200,000 | 5 | 46.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 500,000 | 9 | 62.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 500,000 | 5 | 59.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc1064c-il | 1,000,000 | 9 | 71.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc1064c-il | 1,000,000 | 5 | 73.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||