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KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)
Reynolds number: 100,000
Max Cl/Cd: 62.35 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-kc135winglet-il-100000.txt
Download as CSV file: xf-kc135winglet-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: KC-135 Winglet (supercritical Whitcomb)         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4274   0.09333   0.08841  -0.0305   1.0000   0.0751
  -8.000  -0.4337   0.09085   0.08602  -0.0306   1.0000   0.0772
  -7.750  -0.4434   0.08829   0.08358  -0.0325   1.0000   0.0791
  -7.500  -0.4517   0.08444   0.07981  -0.0416   1.0000   0.0803
  -7.250  -0.4574   0.08136   0.07653  -0.0500   1.0000   0.0810
  -7.000  -0.4481   0.07696   0.07243  -0.0396   1.0000   0.0838
  -6.750  -0.4439   0.07437   0.06988  -0.0379   1.0000   0.0872
  -6.500  -0.4398   0.07067   0.06614  -0.0415   1.0000   0.0920
  -6.250  -0.4314   0.06554   0.06082  -0.0492   1.0000   0.0969
  -6.000  -0.4247   0.06304   0.05844  -0.0457   1.0000   0.1009
  -5.750  -0.4063   0.05850   0.05362  -0.0526   1.0000   0.1116
  -5.500  -0.3964   0.05593   0.05117  -0.0504   1.0000   0.1176
  -5.250  -0.3778   0.05231   0.04743  -0.0533   1.0000   0.1302
  -5.000  -0.3582   0.04924   0.04427  -0.0552   1.0000   0.1465
  -4.750  -0.3361   0.04614   0.04104  -0.0579   1.0000   0.1717
  -4.500  -0.3169   0.04367   0.03857  -0.0586   1.0000   0.2013
  -3.500  -0.1319   0.02876   0.02096  -0.0756   1.0000   0.0929
  -3.250  -0.0922   0.02608   0.01776  -0.0769   1.0000   0.0724
  -3.000  -0.0600   0.02537   0.01654  -0.0767   1.0000   0.0663
  -2.750  -0.0253   0.02328   0.01433  -0.0780   1.0000   0.0631
  -2.500   0.0076   0.02192   0.01282  -0.0785   1.0000   0.0597
  -2.250   0.0395   0.02089   0.01170  -0.0790   1.0000   0.0583
  -2.000   0.0723   0.02002   0.01087  -0.0799   1.0000   0.0589
  -1.750   0.1064   0.01939   0.01024  -0.0813   1.0000   0.0618
  -1.500   0.1402   0.01899   0.00973  -0.0828   1.0000   0.0679
  -1.250   0.1845   0.01686   0.01026  -0.0846   1.0000   0.7863
  -1.000   0.1743   0.01711   0.01064  -0.0746   1.0000   0.8688
  -0.750   0.1596   0.01670   0.01032  -0.0645   1.0000   0.9363
  -0.500   0.1564   0.01645   0.01006  -0.0592   1.0000   1.0000
  -0.250   0.1907   0.01686   0.01025  -0.0618   1.0000   1.0000
   0.000   0.2243   0.01730   0.01054  -0.0642   1.0000   1.0000
   0.250   0.2570   0.01779   0.01090  -0.0665   1.0000   1.0000
   0.500   0.2890   0.01830   0.01133  -0.0686   1.0000   1.0000
   0.750   0.3201   0.01886   0.01183  -0.0707   1.0000   1.0000
   1.000   0.3504   0.01947   0.01240  -0.0726   1.0000   1.0000
   1.250   0.3969   0.01998   0.01289  -0.0774   0.9919   1.0000
   1.500   0.4512   0.02035   0.01327  -0.0833   0.9793   1.0000
   1.750   0.5071   0.02051   0.01347  -0.0892   0.9643   1.0000
   2.000   0.5662   0.02033   0.01337  -0.0950   0.9475   1.0000
   2.250   0.6263   0.01957   0.01275  -0.1000   0.9254   1.0000
   2.500   0.6839   0.01849   0.01181  -0.1039   0.9048   1.0000
   2.750   0.7378   0.01736   0.01085  -0.1070   0.8879   1.0000
   3.000   0.7760   0.01652   0.01021  -0.1072   0.8655   1.0000
   3.250   0.8140   0.01546   0.00929  -0.1068   0.8366   1.0000
   3.500   0.8463   0.01461   0.00853  -0.1053   0.7946   1.0000
   3.750   0.8747   0.01403   0.00789  -0.1030   0.7137   1.0000
   4.000   0.8871   0.01546   0.00758  -0.0979   0.3990   1.0000
   4.250   0.8987   0.01796   0.00883  -0.0954   0.2459   1.0000
   4.500   0.9202   0.01943   0.00990  -0.0946   0.2028   1.0000
   4.750   0.9439   0.02078   0.01100  -0.0940   0.1809   1.0000
   5.000   0.9699   0.02216   0.01225  -0.0938   0.1658   1.0000
   5.250   0.9975   0.02344   0.01352  -0.0938   0.1537   1.0000
   5.500   1.0249   0.02473   0.01487  -0.0938   0.1421   1.0000
   5.750   1.0524   0.02619   0.01641  -0.0938   0.1317   1.0000
   6.000   1.0777   0.02747   0.01772  -0.0936   0.1194   1.0000
   6.250   1.1042   0.02924   0.01944  -0.0937   0.1094   1.0000
   6.500   1.1299   0.03085   0.02138  -0.0931   0.1005   1.0000
   6.750   1.1545   0.03314   0.02393  -0.0926   0.0923   1.0000
   7.000   1.1783   0.03495   0.02585  -0.0921   0.0850   1.0000
   7.250   1.2005   0.03834   0.02965  -0.0912   0.0815   1.0000
   7.500   1.2192   0.04162   0.03357  -0.0894   0.0791   1.0000
   7.750   1.2347   0.04549   0.03803  -0.0875   0.0778   1.0000
   8.000   1.2458   0.04988   0.04301  -0.0852   0.0775   1.0000
   8.250   1.2531   0.05423   0.04789  -0.0828   0.0765   1.0000
   8.500   1.2568   0.05864   0.05276  -0.0803   0.0755   1.0000
   8.750   1.2513   0.06442   0.05909  -0.0773   0.0768   1.0000
   9.000   1.2415   0.07049   0.06556  -0.0746   0.0791   1.0000
   9.250   1.2364   0.07616   0.07145  -0.0727   0.0812   1.0000
   9.750   1.1073   0.07612   0.07192  -0.0523   0.0842   1.0000
  10.000   0.9997   0.08793   0.08414  -0.0507   0.0987   1.0000
  10.250   0.8987   0.11973   0.11602  -0.0671   0.1660   1.0000
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