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KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.52 at α=1°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-kc135winglet-il-1000000.txt
Download as CSV file: xf-kc135winglet-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.4491   0.11698   0.11521  -0.0209   1.0000   0.0058
 -10.500  -0.4443   0.11351   0.11175  -0.0223   1.0000   0.0059
  -7.750  -0.4249   0.07525   0.07371  -0.0375   0.9967   0.0074
  -7.500  -0.3919   0.06554   0.06397  -0.0565   0.9935   0.0076
  -7.250  -0.3630   0.05782   0.05613  -0.0682   0.9899   0.0076
  -7.000  -0.3321   0.05069   0.04884  -0.0776   0.9875   0.0077
  -6.750  -0.3042   0.04212   0.04001  -0.0873   0.9857   0.0080
  -6.500  -0.2731   0.03833   0.03607  -0.0925   0.9848   0.0082
  -6.250  -0.2428   0.03492   0.03250  -0.0963   0.9824   0.0084
  -6.000  -0.2101   0.03150   0.02888  -0.0999   0.9800   0.0087
  -5.750  -0.1755   0.02822   0.02539  -0.1033   0.9780   0.0093
  -5.500  -0.1390   0.02503   0.02193  -0.1062   0.9762   0.0101
  -5.250  -0.1019   0.02293   0.01955  -0.1078   0.9744   0.0108
  -5.000  -0.0632   0.01871   0.01486  -0.1114   0.9730   0.0112
  -4.750  -0.0309   0.01694   0.01298  -0.1134   0.9698   0.0118
  -4.500   0.0003   0.01573   0.01165  -0.1146   0.9654   0.0125
  -4.250   0.0329   0.01458   0.01033  -0.1156   0.9616   0.0138
  -2.750   0.2209   0.00822   0.00325  -0.1190   0.9293   0.0107
  -2.500   0.2537   0.00759   0.00256  -0.1201   0.9225   0.0106
  -2.250   0.2854   0.00719   0.00207  -0.1209   0.9165   0.0114
  -2.000   0.3161   0.00696   0.00179  -0.1215   0.9097   0.0122
  -1.750   0.3455   0.00683   0.00163  -0.1218   0.9024   0.0138
  -1.500   0.3747   0.00674   0.00149  -0.1220   0.8921   0.0144
  -1.250   0.4033   0.00668   0.00138  -0.1220   0.8801   0.0157
  -1.000   0.4428   0.00551   0.00127  -0.1256   0.8656   0.4388
  -0.750   0.4748   0.00510   0.00137  -0.1268   0.8467   0.6562
  -0.500   0.5028   0.00515   0.00140  -0.1266   0.8298   0.6855
  -0.250   0.5308   0.00522   0.00150  -0.1265   0.8164   0.7200
   0.000   0.5591   0.00527   0.00153  -0.1265   0.8043   0.7289
   0.500   0.6147   0.00548   0.00159  -0.1263   0.7621   0.7407
   0.750   0.6424   0.00559   0.00163  -0.1261   0.7375   0.7462
   1.000   0.6700   0.00575   0.00168  -0.1260   0.7073   0.7518
   1.250   0.6965   0.00600   0.00176  -0.1257   0.6544   0.7562
   1.500   0.7207   0.00667   0.00195  -0.1251   0.5431   0.7603
   1.750   0.7448   0.00746   0.00222  -0.1247   0.4226   0.7646
   2.000   0.7696   0.00815   0.00249  -0.1244   0.3227   0.7687
   2.250   0.7951   0.00867   0.00272  -0.1241   0.2540   0.7727
   2.500   0.8210   0.00915   0.00296  -0.1239   0.1972   0.7772
   2.750   0.8470   0.00961   0.00320  -0.1238   0.1499   0.7817
   3.000   0.8732   0.00998   0.00343  -0.1236   0.1163   0.7861
   3.250   0.8998   0.01029   0.00364  -0.1234   0.0974   0.7910
   3.500   0.9267   0.01055   0.00387  -0.1234   0.0867   0.7962
   3.750   0.9536   0.01076   0.00409  -0.1232   0.0789   0.8011
   4.000   0.9801   0.01105   0.00434  -0.1230   0.0699   0.8066
   4.250   1.0072   0.01124   0.00456  -0.1229   0.0660   0.8119
   4.500   1.0335   0.01151   0.00482  -0.1227   0.0603   0.8172
   4.750   1.0602   0.01175   0.00508  -0.1226   0.0566   0.8231
   5.000   1.0867   0.01195   0.00532  -0.1224   0.0537   0.8285
   5.250   1.1128   0.01223   0.00560  -0.1221   0.0497   0.8347
   5.500   1.1389   0.01251   0.00591  -0.1219   0.0458   0.8408
   5.750   1.1651   0.01271   0.00616  -0.1216   0.0425   0.8473
   6.000   1.1905   0.01306   0.00650  -0.1213   0.0353   0.8541
   6.250   1.2151   0.01347   0.00689  -0.1208   0.0272   0.8614
   6.500   1.2400   0.01385   0.00730  -0.1203   0.0249   0.8695
   6.750   1.2643   0.01428   0.00777  -0.1197   0.0231   0.8789
   7.000   1.2879   0.01478   0.00835  -0.1189   0.0216   0.8896
   7.250   1.3104   0.01539   0.00908  -0.1179   0.0203   0.9021
   7.500   1.3336   0.01569   0.00947  -0.1171   0.0198   0.9191
   7.750   1.3516   0.01593   0.00984  -0.1151   0.0193   1.0000
   8.000   1.3759   0.01646   0.01044  -0.1146   0.0187   1.0000
   8.250   1.3998   0.01698   0.01102  -0.1141   0.0180   1.0000
   8.500   1.4233   0.01752   0.01161  -0.1135   0.0172   1.0000
   8.750   1.4458   0.01819   0.01233  -0.1127   0.0164   1.0000
   9.000   1.4664   0.01909   0.01332  -0.1116   0.0155   1.0000
   9.250   1.4840   0.02036   0.01474  -0.1100   0.0146   1.0000
   9.500   1.5079   0.02068   0.01512  -0.1096   0.0143   1.0000
   9.750   1.5310   0.02108   0.01558  -0.1089   0.0138   1.0000
  10.000   1.5536   0.02152   0.01609  -0.1083   0.0130   1.0000
  10.250   1.5763   0.02190   0.01650  -0.1077   0.0121   1.0000
  10.500   1.5964   0.02258   0.01720  -0.1067   0.0110   1.0000
  10.750   1.6160   0.02328   0.01799  -0.1056   0.0100   1.0000
  11.000   1.6398   0.02344   0.01816  -0.1051   0.0088   1.0000
  11.250   1.6601   0.02400   0.01870  -0.1042   0.0074   1.0000
  11.500   1.6774   0.02485   0.01964  -0.1026   0.0065   1.0000
  11.750   1.6942   0.02570   0.02055  -0.1011   0.0058   1.0000
  12.000   1.7082   0.02678   0.02171  -0.0992   0.0052   1.0000
  12.250   1.7161   0.02829   0.02337  -0.0963   0.0048   1.0000
  12.500   1.7253   0.02944   0.02465  -0.0935   0.0046   1.0000
  12.750   1.7305   0.03067   0.02602  -0.0902   0.0045   1.0000
  13.000   1.7339   0.03203   0.02753  -0.0867   0.0043   1.0000
  13.250   1.7364   0.03354   0.02918  -0.0835   0.0042   1.0000
  13.500   1.7374   0.03524   0.03102  -0.0803   0.0041   1.0000
  13.750   1.7373   0.03712   0.03305  -0.0773   0.0040   1.0000
  14.000   1.7357   0.03920   0.03529  -0.0745   0.0039   1.0000
  14.250   1.7324   0.04158   0.03781  -0.0719   0.0038   1.0000
  14.500   1.7265   0.04431   0.04071  -0.0696   0.0038   1.0000
  14.750   1.7185   0.04747   0.04403  -0.0677   0.0037   1.0000
  15.000   1.7082   0.05106   0.04778  -0.0662   0.0036   1.0000
  15.250   1.6948   0.05534   0.05223  -0.0654   0.0036   1.0000
  15.500   1.6780   0.06040   0.05747  -0.0654   0.0036   1.0000
  15.750   1.6593   0.06622   0.06348  -0.0664   0.0036   1.0000
  16.000   1.6363   0.07345   0.07089  -0.0689   0.0036   1.0000
  16.250   1.6076   0.08280   0.08044  -0.0735   0.0036   1.0000
  16.500   1.5694   0.09579   0.09367  -0.0813   0.0037   1.0000
  16.750   1.5034   0.11672   0.11491  -0.0934   0.0039   1.0000
  17.000   1.4165   0.14149   0.13990  -0.1068   0.0042   1.0000
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