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 | ||
(ames01-il) NASA/AMES A-01 AIRFOIL | NASA/AMES/Hicks A-01 transonic rotorcraft airfoil Max thickness 10.3% at 35% chord Max camber 1.4% at 15% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (ames01-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ames01-il | 50,000 | 9 | 25.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 50,000 | 5 | 27.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 100,000 | 9 | 35 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 100,000 | 5 | 40.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 200,000 | 9 | 53.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 200,000 | 5 | 55.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 500,000 | 9 | 76.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 500,000 | 5 | 74.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ames01-il | 1,000,000 | 9 | 93.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ames01-il | 1,000,000 | 5 | 88.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||