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KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)

KC-135 Winglet (supercritical Whitcomb) - Boeing KC-135 winglet airfoil designed by Richard T. Whitcomb


Airfoil kc135winglet-il
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
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Selig format dat file

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Polars for KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)

PlotAirfoilReynolds #NcritMax Cl/CdDescriptionSource 
   kc135winglet-il50,000940.8 at α=4.5°Mach=0 Ncrit=9Xfoil predictionDetails
   kc135winglet-il50,000540.9 at α=4.25°Mach=0 Ncrit=5Xfoil predictionDetails
   kc135winglet-il100,000962.3 at α=3.75°Mach=0 Ncrit=9Xfoil predictionDetails
   kc135winglet-il100,000559.2 at α=3.25°Mach=0 Ncrit=5Xfoil predictionDetails
   kc135winglet-il200,000985.6 at α=3.25°Mach=0 Ncrit=9Xfoil predictionDetails
   kc135winglet-il200,000573.2 at α=2°Mach=0 Ncrit=5Xfoil predictionDetails
   kc135winglet-il500,0009103.4 at α=2°Mach=0 Ncrit=9Xfoil predictionDetails
   kc135winglet-il500,000588.7 at α=0.75°Mach=0 Ncrit=5Xfoil predictionDetails
   kc135winglet-il1,000,0009116.5 at α=1°Mach=0 Ncrit=9Xfoil predictionDetails
   kc135winglet-il1,000,000589.1 at α=5°Mach=0 Ncrit=5Xfoil predictionDetails
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