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KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)
Reynolds number: 500,000
Max Cl/Cd: 103.37 at α=2°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-kc135winglet-il-500000.txt
Download as CSV file: xf-kc135winglet-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3230   0.09142   0.08922  -0.0324   1.0000   0.0103
  -9.250  -0.3237   0.08830   0.08612  -0.0323   1.0000   0.0106
  -9.000  -0.4170   0.09475   0.09240  -0.0327   1.0000   0.0095
  -8.750  -0.4150   0.09199   0.08967  -0.0319   1.0000   0.0097
  -8.500  -0.4135   0.08945   0.08715  -0.0315   1.0000   0.0100
  -8.250  -0.4157   0.08680   0.08455  -0.0312   1.0000   0.0101
  -8.000  -0.4229   0.08456   0.08235  -0.0299   1.0000   0.0102
  -7.750  -0.4382   0.08295   0.08081  -0.0267   1.0000   0.0102
  -7.500  -0.4525   0.08116   0.07908  -0.0243   1.0000   0.0103
  -7.250  -0.4424   0.07671   0.07465  -0.0296   0.9983   0.0104
  -7.000  -0.4133   0.06960   0.06751  -0.0431   0.9952   0.0106
  -6.750  -0.3837   0.06262   0.06043  -0.0551   0.9915   0.0108
  -6.500  -0.3519   0.05631   0.05400  -0.0650   0.9884   0.0112
  -6.250  -0.3168   0.05037   0.04789  -0.0736   0.9864   0.0116
  -6.000  -0.2799   0.04491   0.04220  -0.0807   0.9844   0.0122
  -5.750  -0.2381   0.04038   0.03727  -0.0855   0.9809   0.0130
  -5.500  -0.2023   0.03472   0.03129  -0.0911   0.9788   0.0134
  -5.250  -0.1700   0.03162   0.02811  -0.0952   0.9773   0.0141
  -5.000  -0.1330   0.02891   0.02520  -0.0990   0.9762   0.0152
  -4.750  -0.0893   0.02786   0.02369  -0.1012   0.9752   0.0177
  -4.500  -0.0510   0.02308   0.01869  -0.1059   0.9747   0.0190
  -4.250  -0.0132   0.02127   0.01675  -0.1090   0.9741   0.0211
  -4.000   0.0229   0.02214   0.01727  -0.1095   0.9707   0.0244
  -2.750   0.2100   0.01203   0.00624  -0.1191   0.9622   0.0181
  -2.500   0.2477   0.01049   0.00467  -0.1209   0.9607   0.0133
  -2.250   0.2820   0.00967   0.00384  -0.1223   0.9563   0.0126
  -2.000   0.3172   0.00909   0.00320  -0.1239   0.9519   0.0126
  -1.750   0.3521   0.00866   0.00271  -0.1253   0.9481   0.0145
  -1.500   0.3831   0.00847   0.00251  -0.1259   0.9427   0.0216
  -1.250   0.4289   0.00667   0.00253  -0.1315   0.9399   0.6574
  -1.000   0.4572   0.00665   0.00258  -0.1311   0.9330   0.7034
  -0.750   0.4828   0.00668   0.00262  -0.1301   0.9218   0.7314
  -0.500   0.5057   0.00680   0.00279  -0.1281   0.9077   0.7686
  -0.250   0.5302   0.00678   0.00271  -0.1268   0.8899   0.7756
   0.000   0.5570   0.00680   0.00265  -0.1262   0.8724   0.7814
   0.250   0.5838   0.00682   0.00263  -0.1257   0.8598   0.7859
   0.500   0.6111   0.00686   0.00265  -0.1254   0.8465   0.7913
   0.750   0.6388   0.00691   0.00265  -0.1252   0.8288   0.7966
   1.000   0.6654   0.00694   0.00265  -0.1247   0.8077   0.8003
   1.250   0.6925   0.00702   0.00266  -0.1243   0.7882   0.8046
   1.500   0.7200   0.00713   0.00270  -0.1241   0.7642   0.8091
   1.750   0.7467   0.00725   0.00274  -0.1238   0.7333   0.8132
   2.000   0.7722   0.00747   0.00282  -0.1231   0.6826   0.8177
   2.250   0.7942   0.00818   0.00297  -0.1219   0.5626   0.8228
   2.500   0.8145   0.00925   0.00336  -0.1207   0.4158   0.8273
   2.750   0.8364   0.01018   0.00375  -0.1199   0.2995   0.8320
   3.000   0.8605   0.01090   0.00409  -0.1195   0.2202   0.8376
   3.250   0.8845   0.01150   0.00445  -0.1190   0.1619   0.8425
   3.500   0.9092   0.01201   0.00479  -0.1186   0.1273   0.8483
   3.750   0.9348   0.01240   0.00511  -0.1183   0.1070   0.8545
   4.000   0.9599   0.01276   0.00543  -0.1179   0.0938   0.8606
   4.250   0.9854   0.01315   0.00580  -0.1175   0.0838   0.8675
   4.500   1.0104   0.01342   0.00612  -0.1170   0.0777   0.8741
   4.750   1.0350   0.01391   0.00660  -0.1165   0.0715   0.8819
   5.000   1.0601   0.01411   0.00691  -0.1160   0.0684   0.8900
   5.250   1.0849   0.01438   0.00723  -0.1155   0.0643   0.8991
   5.500   1.1078   0.01490   0.00777  -0.1146   0.0593   0.9098
   5.750   1.1318   0.01498   0.00796  -0.1138   0.0565   0.9231
   6.000   1.1516   0.01508   0.00813  -0.1122   0.0514   0.9485
   6.250   1.1756   0.01540   0.00849  -0.1116   0.0446   1.0000
   6.500   1.2012   0.01603   0.00909  -0.1114   0.0356   1.0000
   6.750   1.2269   0.01656   0.00963  -0.1112   0.0307   1.0000
   7.000   1.2496   0.01750   0.01061  -0.1104   0.0276   1.0000
   7.250   1.2741   0.01807   0.01126  -0.1100   0.0260   1.0000
   7.500   1.2987   0.01857   0.01179  -0.1096   0.0240   1.0000
   7.750   1.3211   0.01936   0.01259  -0.1089   0.0220   1.0000
   8.000   1.3411   0.02049   0.01383  -0.1077   0.0206   1.0000
   8.250   1.3651   0.02093   0.01436  -0.1073   0.0194   1.0000
   8.500   1.3883   0.02144   0.01494  -0.1067   0.0180   1.0000
   8.750   1.4099   0.02216   0.01573  -0.1059   0.0170   1.0000
   9.000   1.4295   0.02311   0.01674  -0.1048   0.0157   1.0000
   9.250   1.4468   0.02434   0.01810  -0.1034   0.0146   1.0000
   9.500   1.4715   0.02446   0.01830  -0.1031   0.0137   1.0000
   9.750   1.4942   0.02483   0.01874  -0.1025   0.0127   1.0000
  10.000   1.5170   0.02515   0.01911  -0.1020   0.0116   1.0000
  10.250   1.5363   0.02589   0.01990  -0.1010   0.0105   1.0000
  10.500   1.5571   0.02640   0.02050  -0.1001   0.0095   1.0000
  10.750   1.5782   0.02684   0.02103  -0.0992   0.0081   1.0000
  11.000   1.5968   0.02754   0.02179  -0.0980   0.0068   1.0000
  11.250   1.6131   0.02843   0.02280  -0.0964   0.0051   1.0000
  11.750   1.6333   0.03121   0.02575  -0.0916   0.0024   1.0000
  12.000   1.6386   0.03268   0.02740  -0.0884   0.0022   1.0000
  12.250   1.6414   0.03434   0.02923  -0.0850   0.0020   1.0000
  12.500   1.6428   0.03616   0.03125  -0.0817   0.0019   1.0000
  12.750   1.6420   0.03824   0.03353  -0.0785   0.0018   1.0000
  13.000   1.6398   0.04050   0.03600  -0.0755   0.0017   1.0000
  13.250   1.6352   0.04309   0.03881  -0.0726   0.0016   1.0000
  13.500   1.6282   0.04603   0.04197  -0.0701   0.0015   1.0000
  13.750   1.6193   0.04934   0.04549  -0.0680   0.0015   1.0000
  14.000   1.6085   0.05303   0.04941  -0.0665   0.0015   1.0000
  14.250   1.5949   0.05737   0.05397  -0.0656   0.0014   1.0000
  14.500   1.5782   0.06247   0.05929  -0.0656   0.0014   1.0000
  14.750   1.5586   0.06852   0.06555  -0.0668   0.0014   1.0000
  15.000   1.5346   0.07607   0.07333  -0.0697   0.0014   1.0000
  15.250   1.5053   0.08595   0.08342  -0.0751   0.0015   1.0000
  15.500   1.4678   0.09979   0.09751  -0.0839   0.0015   1.0000
  15.750   1.4193   0.11760   0.11557  -0.0941   0.0018   1.0000
  16.000   1.3638   0.13572   0.13386  -0.1036   0.0021   1.0000
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