KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)
KC-135 Winglet (supercritical Whitcomb) - Boeing KC-135 winglet airfoil designed by Richard T. Whitcomb
| Details | Dat file | Parser | |
|
(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 Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
KC-135 Winglet (supercritical Whitcomb) 1.000 -.0020 .9750 0.0038 .9500 0.0089 .9250 0.0138 .9000 0.0184 .8750 0.0228 .8500 0.0270 .8250 0.0311 .8000 0.0349 .7750 0.0384 .7500 0.0419 .7250 0.0451 .7000 0.0481 .6750 0.0508 .6500 0.0533 .6250 0.0554 .6000 0.0572 .5750 0.0587 .5500 0.0599 .5000 0.0618 .4500 0.0627 .4000 0.0628 .3500 0.0621 .3000 0.0605 .2500 0.0581 .2000 0.0547 .1750 0.0525 .1500 0.0499 .1250 0.0469 .1000 0.0433 .0750 0.0389 .0500 0.0333 .0375 0.0296 .0250 0.0249 .0125 0.0179 .0050 0.0119 .0020 0.0077 .000 0.0000 .0020 -.0032 .0050 -.0041 .0125 -.0060 .0250 -.0077 .0375 -.0090 .0500 -.0100 .0750 -.0118 .1000 -.0132 .1250 -.0144 .1500 -.0154 .1750 -.0161 .2000 -.0167 .2500 -.0175 .3000 -.0176 .3500 -.0174 .4000 -.0168 .4500 -.0158 .5000 -.0144 .5500 -.0122 .5750 -.0106 .6000 -.0090 .6250 -.0071 .6500 -.0052 .6750 -.0033 .7000 -.0015 .7250 0.0004 .7500 0.0020 .7750 0.0036 .8000 0.0049 .8250 0.0060 .8500 0.0065 .8750 0.0064 .9000 0.0059 .9250 0.0045 .9500 0.0021 .9750 -.0013 1.000 -.0067 |
No parser warnings |
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for KC-135 Winglet (supercritical Whitcomb) (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 | |||||||