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KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)
Reynolds number: 200,000
Max Cl/Cd: 85.6 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-kc135winglet-il-200000.txt
Download as CSV file: xf-kc135winglet-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4314   0.09966   0.09605  -0.0367   1.0000   0.0287
  -8.750  -0.4344   0.09664   0.09309  -0.0377   1.0000   0.0288
  -8.500  -0.4380   0.09090   0.08742  -0.0361   1.0000   0.0295
  -8.250  -0.4305   0.08803   0.08456  -0.0331   1.0000   0.0307
  -8.000  -0.4336   0.08567   0.08225  -0.0318   1.0000   0.0314
  -7.750  -0.4398   0.08333   0.07998  -0.0306   1.0000   0.0321
  -7.500  -0.4440   0.08061   0.07732  -0.0307   1.0000   0.0328
  -7.250  -0.4483   0.07758   0.07433  -0.0318   1.0000   0.0336
  -7.000  -0.4508   0.07392   0.07072  -0.0346   1.0000   0.0342
  -6.750  -0.4500   0.07002   0.06680  -0.0377   1.0000   0.0350
  -6.500  -0.4450   0.06599   0.06272  -0.0409   1.0000   0.0361
  -6.250  -0.4331   0.06171   0.05831  -0.0451   1.0000   0.0377
  -6.000  -0.4067   0.05904   0.05512  -0.0512   1.0000   0.0396
  -5.750  -0.3916   0.05230   0.04819  -0.0550   1.0000   0.0406
  -5.500  -0.3790   0.04824   0.04424  -0.0555   1.0000   0.0419
  -5.250  -0.3611   0.04536   0.04132  -0.0566   1.0000   0.0437
  -5.000  -0.3363   0.04239   0.03819  -0.0589   0.9999   0.0466
  -3.000  -0.0008   0.02102   0.01378  -0.0868   0.9880   0.0409
  -2.750   0.0383   0.01901   0.01166  -0.0887   0.9876   0.0341
  -2.500   0.0782   0.01774   0.01020  -0.0905   0.9866   0.0308
  -2.250   0.1181   0.01689   0.00940  -0.0932   0.9855   0.0345
  -2.000   0.1602   0.01609   0.00861  -0.0962   0.9845   0.0359
  -1.750   0.1998   0.01548   0.00796  -0.0989   0.9813   0.0374
  -1.500   0.2412   0.01503   0.00739  -0.1019   0.9782   0.0418
  -1.250   0.2912   0.01322   0.00792  -0.1069   0.9809   0.7536
  -1.000   0.3119   0.01362   0.00845  -0.1039   0.9751   0.8147
  -0.750   0.3370   0.01377   0.00863  -0.1023   0.9712   0.8474
  -0.500   0.3542   0.01382   0.00872  -0.0994   0.9640   0.8725
  -0.250   0.3917   0.01381   0.00865  -0.1016   0.9606   0.8809
   0.000   0.4235   0.01374   0.00857  -0.1025   0.9550   0.8876
   0.250   0.4624   0.01355   0.00836  -0.1047   0.9481   0.8945
   0.500   0.5037   0.01309   0.00790  -0.1069   0.9404   0.9000
   0.750   0.5520   0.01234   0.00717  -0.1101   0.9314   0.9049
   1.000   0.5898   0.01162   0.00646  -0.1110   0.9178   0.9102
   1.250   0.6204   0.01109   0.00595  -0.1105   0.9040   0.9164
   1.500   0.6483   0.01079   0.00569  -0.1099   0.8913   0.9235
   1.750   0.6742   0.01053   0.00549  -0.1089   0.8787   0.9315
   2.000   0.6996   0.01024   0.00523  -0.1077   0.8635   0.9400
   2.250   0.7246   0.00992   0.00493  -0.1063   0.8446   0.9504
   2.500   0.7471   0.00967   0.00471  -0.1045   0.8206   0.9663
   2.750   0.7759   0.00946   0.00451  -0.1041   0.7908   1.0000
   3.000   0.8066   0.00950   0.00447  -0.1044   0.7472   1.0000
   3.250   0.8346   0.00975   0.00441  -0.1039   0.6563   1.0000
   3.500   0.8513   0.01122   0.00470  -0.1017   0.4431   1.0000
   3.750   0.8690   0.01306   0.00555  -0.1008   0.2632   1.0000
   4.000   0.8923   0.01440   0.00633  -0.1008   0.1785   1.0000
   4.250   0.9182   0.01537   0.00709  -0.1009   0.1485   1.0000
   4.500   0.9446   0.01622   0.00786  -0.1010   0.1323   1.0000
   4.750   0.9706   0.01709   0.00867  -0.1010   0.1208   1.0000
   5.000   0.9961   0.01797   0.00945  -0.1010   0.1100   1.0000
   5.250   1.0233   0.01850   0.01008  -0.1011   0.1017   1.0000
   5.500   1.0482   0.01947   0.01101  -0.1009   0.0947   1.0000
   5.750   1.0743   0.02009   0.01171  -0.1008   0.0876   1.0000
   6.000   1.0988   0.02110   0.01273  -0.1005   0.0807   1.0000
   6.250   1.1240   0.02176   0.01347  -0.1002   0.0733   1.0000
   6.500   1.1480   0.02303   0.01484  -0.0997   0.0660   1.0000
   6.750   1.1719   0.02407   0.01588  -0.0992   0.0596   1.0000
   7.000   1.1963   0.02592   0.01789  -0.0986   0.0551   1.0000
   7.250   1.2210   0.02738   0.01954  -0.0980   0.0518   1.0000
   7.500   1.2445   0.02865   0.02090  -0.0974   0.0490   1.0000
   7.750   1.2669   0.03188   0.02429  -0.0970   0.0462   1.0000
   8.000   1.2885   0.03367   0.02644  -0.0959   0.0453   1.0000
   8.250   1.3080   0.03613   0.02932  -0.0945   0.0442   1.0000
   8.500   1.3240   0.03925   0.03289  -0.0927   0.0434   1.0000
   8.750   1.3364   0.04248   0.03660  -0.0905   0.0422   1.0000
   9.000   1.3474   0.04527   0.03975  -0.0883   0.0406   1.0000
   9.250   1.3569   0.04800   0.04277  -0.0862   0.0393   1.0000
   9.500   1.3733   0.04878   0.04351  -0.0853   0.0373   1.0000
  10.000   1.3560   0.05788   0.05347  -0.0780   0.0352   1.0000
  10.250   1.3410   0.06188   0.05789  -0.0737   0.0346   1.0000
  10.500   1.3178   0.06587   0.06218  -0.0689   0.0345   1.0000
  10.750   1.2924   0.07025   0.06682  -0.0653   0.0345   1.0000
  11.000   1.2657   0.07534   0.07212  -0.0633   0.0347   1.0000
  11.250   1.2390   0.08114   0.07811  -0.0631   0.0350   1.0000
  11.500   1.2121   0.08787   0.08496  -0.0646   0.0354   1.0000
  11.750   1.1865   0.09580   0.09297  -0.0674   0.0359   1.0000
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