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KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)
Reynolds number: 1,000,000
Max Cl/Cd: 89.15 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-kc135winglet-il-1000000-n5.txt
Download as CSV file: xf-kc135winglet-il-1000000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4270   0.09127   0.08960  -0.0305   1.0000   0.0051
  -8.750  -0.4270   0.08823   0.08658  -0.0311   1.0000   0.0052
  -8.500  -0.4280   0.08517   0.08355  -0.0316   0.9997   0.0054
  -8.250  -0.4165   0.08060   0.07898  -0.0366   0.9966   0.0059
  -8.000  -0.4020   0.07446   0.07284  -0.0446   0.9907   0.0065
  -7.750  -0.3792   0.06729   0.06568  -0.0567   0.9867   0.0066
  -7.500  -0.3540   0.05918   0.05748  -0.0711   0.9797   0.0066
  -7.250  -0.3277   0.05260   0.05078  -0.0804   0.9754   0.0066
  -7.000  -0.3030   0.04720   0.04523  -0.0864   0.9693   0.0067
  -6.750  -0.2754   0.04223   0.04008  -0.0915   0.9643   0.0067
  -6.500  -0.2475   0.03777   0.03541  -0.0956   0.9595   0.0067
  -6.250  -0.2196   0.03376   0.03119  -0.0986   0.9534   0.0067
  -6.000  -0.1897   0.03007   0.02726  -0.1014   0.9482   0.0067
  -5.750  -0.1598   0.02674   0.02367  -0.1036   0.9423   0.0067
  -5.500  -0.1288   0.02372   0.02037  -0.1055   0.9362   0.0067
  -5.250  -0.0971   0.02101   0.01738  -0.1073   0.9309   0.0067
  -5.000  -0.0651   0.01866   0.01475  -0.1089   0.9252   0.0067
  -4.750  -0.0330   0.01662   0.01242  -0.1102   0.9198   0.0067
  -4.500   0.0003   0.01376   0.00930  -0.1123   0.9150   0.0060
  -4.250   0.0326   0.01197   0.00725  -0.1132   0.9095   0.0056
  -4.000   0.0639   0.01073   0.00582  -0.1138   0.9042   0.0057
  -3.750   0.0948   0.00991   0.00488  -0.1144   0.8981   0.0059
  -3.500   0.1250   0.00941   0.00427  -0.1149   0.8917   0.0064
  -3.250   0.1548   0.00914   0.00392  -0.1153   0.8853   0.0067
  -3.000   0.1860   0.00856   0.00327  -0.1162   0.8786   0.0069
  -2.750   0.2178   0.00804   0.00272  -0.1172   0.8723   0.0073
  -2.500   0.2485   0.00775   0.00242  -0.1180   0.8655   0.0081
  -2.250   0.2793   0.00751   0.00213  -0.1187   0.8595   0.0080
  -2.000   0.3101   0.00730   0.00189  -0.1194   0.8535   0.0078
  -1.750   0.3401   0.00717   0.00170  -0.1198   0.8459   0.0076
  -1.500   0.3697   0.00707   0.00155  -0.1202   0.8324   0.0075
  -1.250   0.3989   0.00701   0.00142  -0.1204   0.8140   0.0075
  -1.000   0.4274   0.00703   0.00132  -0.1205   0.7900   0.0074
  -0.750   0.4555   0.00710   0.00125  -0.1205   0.7598   0.0075
  -0.500   0.4836   0.00718   0.00120  -0.1205   0.7230   0.0076
  -0.250   0.5116   0.00731   0.00117  -0.1206   0.6861   0.0078
   0.000   0.5395   0.00747   0.00118  -0.1206   0.6421   0.0084
   0.250   0.5782   0.00683   0.00139  -0.1246   0.5258   0.5768
   0.500   0.6038   0.00755   0.00176  -0.1246   0.3818   0.6728
   0.750   0.6300   0.00804   0.00199  -0.1245   0.3003   0.7032
   1.000   0.6570   0.00839   0.00213  -0.1245   0.2518   0.7093
   1.250   0.6841   0.00869   0.00228  -0.1245   0.2115   0.7130
   1.500   0.7112   0.00899   0.00243  -0.1244   0.1756   0.7165
   1.750   0.7384   0.00926   0.00257  -0.1244   0.1490   0.7205
   2.000   0.7654   0.00956   0.00274  -0.1243   0.1194   0.7243
   2.250   0.7924   0.00986   0.00292  -0.1243   0.0946   0.7275
   2.500   0.8198   0.01005   0.00308  -0.1243   0.0850   0.7311
   2.750   0.8473   0.01023   0.00324  -0.1242   0.0776   0.7350
   3.000   0.8745   0.01044   0.00341  -0.1242   0.0700   0.7388
   3.250   0.9019   0.01062   0.00360  -0.1241   0.0647   0.7426
   3.500   0.9289   0.01083   0.00379  -0.1241   0.0583   0.7470
   3.750   0.9560   0.01105   0.00400  -0.1240   0.0531   0.7518
   4.000   0.9829   0.01127   0.00420  -0.1239   0.0486   0.7564
   4.250   1.0096   0.01150   0.00445  -0.1237   0.0439   0.7615
   4.500   1.0365   0.01171   0.00467  -0.1236   0.0417   0.7665
   4.750   1.0631   0.01195   0.00492  -0.1234   0.0378   0.7711
   5.000   1.0894   0.01222   0.00519  -0.1232   0.0334   0.7761
   5.250   1.1154   0.01253   0.00549  -0.1230   0.0260   0.7813
   5.500   1.1408   0.01292   0.00584  -0.1226   0.0208   0.7861
   5.750   1.1667   0.01322   0.00618  -0.1223   0.0184   0.7915
   6.000   1.1925   0.01352   0.00652  -0.1220   0.0178   0.7969
   6.250   1.2181   0.01383   0.00688  -0.1217   0.0173   0.8024
   6.500   1.2435   0.01417   0.00728  -0.1213   0.0168   0.8083
   6.750   1.2685   0.01454   0.00770  -0.1209   0.0161   0.8138
   7.000   1.2932   0.01494   0.00815  -0.1204   0.0152   0.8198
   7.250   1.3177   0.01538   0.00862  -0.1199   0.0143   0.8257
   7.500   1.3418   0.01584   0.00917  -0.1193   0.0135   0.8314
   7.750   1.3654   0.01636   0.00978  -0.1186   0.0129   0.8377
   8.000   1.3890   0.01683   0.01033  -0.1180   0.0126   0.8443
   8.250   1.4131   0.01720   0.01077  -0.1174   0.0124   0.8520
   8.500   1.4366   0.01760   0.01126  -0.1168   0.0122   0.8604
   8.750   1.4599   0.01801   0.01177  -0.1161   0.0119   0.8704
   9.250   1.5050   0.01880   0.01275  -0.1145   0.0109   0.9001
   9.500   1.5251   0.01914   0.01319  -0.1132   0.0100   0.9298
   9.750   1.5442   0.01955   0.01366  -0.1117   0.0092   1.0000
  10.000   1.5657   0.02017   0.01433  -0.1108   0.0084   1.0000
  10.250   1.5876   0.02068   0.01492  -0.1100   0.0078   1.0000
  10.500   1.6087   0.02127   0.01554  -0.1091   0.0060   1.0000
  10.750   1.6276   0.02211   0.01636  -0.1079   0.0044   1.0000
  11.000   1.6459   0.02298   0.01730  -0.1065   0.0036   1.0000
  11.250   1.6635   0.02387   0.01828  -0.1051   0.0033   1.0000
  11.500   1.6802   0.02480   0.01932  -0.1035   0.0031   1.0000
  11.750   1.6956   0.02581   0.02044  -0.1017   0.0029   1.0000
  12.000   1.7095   0.02688   0.02163  -0.0997   0.0027   1.0000
  12.250   1.7214   0.02802   0.02291  -0.0974   0.0025   1.0000
  12.500   1.7307   0.02922   0.02424  -0.0948   0.0024   1.0000
  12.750   1.7366   0.03048   0.02564  -0.0916   0.0023   1.0000
  13.000   1.7394   0.03191   0.02721  -0.0880   0.0022   1.0000
  13.250   1.7437   0.03326   0.02869  -0.0849   0.0022   1.0000
  13.500   1.7467   0.03478   0.03036  -0.0819   0.0022   1.0000
  13.750   1.7487   0.03645   0.03217  -0.0790   0.0021   1.0000
  14.000   1.7490   0.03833   0.03419  -0.0763   0.0021   1.0000
  14.250   1.7479   0.04043   0.03644  -0.0737   0.0021   1.0000
  14.500   1.7451   0.04279   0.03895  -0.0713   0.0020   1.0000
  14.750   1.7400   0.04551   0.04184  -0.0692   0.0020   1.0000
  15.000   1.7331   0.04857   0.04506  -0.0674   0.0020   1.0000
  15.250   1.7242   0.05205   0.04871  -0.0661   0.0020   1.0000
  15.500   1.7123   0.05617   0.05299  -0.0654   0.0019   1.0000
  15.750   1.6973   0.06095   0.05794  -0.0653   0.0019   1.0000
  16.000   1.6787   0.06671   0.06389  -0.0663   0.0019   1.0000
  16.250   1.6551   0.07393   0.07130  -0.0687   0.0019   1.0000
  16.500   1.6240   0.08359   0.08117  -0.0734   0.0019   1.0000
  16.750   1.5749   0.09907   0.09691  -0.0829   0.0020   1.0000
  17.000   1.3920   0.14796   0.14628  -0.1105   0.0023   1.0000
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