Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(k3311sm-il) K3311 (smoothed) | Leon Kincaid K3311 airfoil (smoothed) Max thickness 11% at 30.6% chord Max camber 3.2% at 41.6% chord | Remove Airfoil details Airfoil plotter |
(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 |
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Polars for (k3311sm-il,kc135winglet-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| k3311sm-il | 50,000 | 9 | 33.9 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311sm-il | 50,000 | 5 | 36.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311sm-il | 100,000 | 9 | 55.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311sm-il | 100,000 | 5 | 57 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311sm-il | 200,000 | 9 | 77.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311sm-il | 200,000 | 5 | 76.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311sm-il | 500,000 | 9 | 108.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311sm-il | 500,000 | 5 | 101.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k3311sm-il | 1,000,000 | 9 | 130.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k3311sm-il | 1,000,000 | 5 | 118.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
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