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 | ||
(v43015-il) BOEING VERTOL V43015-2.48 AIRFOIL | Boeing-Vertol V43015-2.48 rotorcraft airfoil Max thickness 15% at 30% chord Max camber 3.7% at 15% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (v43015-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| v43015-il | 50,000 | 9 | 23.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 9 | 36.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 100,000 | 5 | 39.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 9 | 51.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 200,000 | 5 | 53.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 9 | 74.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 500,000 | 5 | 76.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 9 | 98.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v43015-il | 1,000,000 | 5 | 95 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||