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 | ||
(kc135winglet-il) KC-135 Winglet (supercritical Whitcomb) | Boeing KC-135 winglet airfoil designed by Richard T. Whitcomb Max thickness 8% at 40% chord Max camber 2.7% at 65% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (kc135winglet-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| kc135winglet-il | 50,000 | 9 | 40.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 50,000 | 5 | 40.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 100,000 | 9 | 62.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 100,000 | 5 | 59.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 200,000 | 9 | 85.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 200,000 | 5 | 73.2 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 500,000 | 9 | 103.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 500,000 | 5 | 88.7 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 1,000,000 | 9 | 116.5 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 1,000,000 | 5 | 89.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||