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 | ||
(v13009-il) BOEING VERTOL V(1.95)3009-1.25 AIRFOIL | Boeing-Vertol V(1.9)3006-1.25 rotorcraft airfoil Max thickness 9% at 30.1% chord Max camber 1.3% at 20.1% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (v13009-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| v13009-il | 50,000 | 9 | 26.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 50,000 | 5 | 28.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 100,000 | 9 | 36.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 100,000 | 5 | 39.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 200,000 | 9 | 49.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 200,000 | 5 | 53.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 500,000 | 9 | 72.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 500,000 | 5 | 71.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13009-il | 1,000,000 | 9 | 88.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13009-il | 1,000,000 | 5 | 86.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||