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KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)
Reynolds number: 500,000
Max Cl/Cd: 88.67 at α=0.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-kc135winglet-il-500000-n5.txt
Download as CSV file: xf-kc135winglet-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4253   0.08898   0.08665  -0.0326   1.0000   0.0093
  -8.500  -0.4293   0.08559   0.08331  -0.0332   1.0000   0.0093
  -8.250  -0.4384   0.08295   0.08072  -0.0322   1.0000   0.0094
  -8.000  -0.4283   0.07776   0.07555  -0.0382   0.9966   0.0094
  -7.750  -0.4050   0.07049   0.06828  -0.0505   0.9919   0.0094
  -7.500  -0.3859   0.06321   0.06094  -0.0621   0.9876   0.0097
  -7.250  -0.3650   0.05866   0.05632  -0.0685   0.9839   0.0099
  -7.000  -0.3408   0.05366   0.05122  -0.0755   0.9796   0.0102
  -6.750  -0.3118   0.04836   0.04576  -0.0826   0.9768   0.0104
  -6.500  -0.2813   0.04348   0.04068  -0.0885   0.9742   0.0107
  -6.250  -0.2524   0.03917   0.03616  -0.0926   0.9695   0.0111
  -6.000  -0.2192   0.03494   0.03166  -0.0967   0.9664   0.0117
  -5.750  -0.1785   0.03115   0.02735  -0.0996   0.9641   0.0127
  -5.500  -0.1462   0.02681   0.02280  -0.1040   0.9622   0.0133
  -5.250  -0.1154   0.02484   0.02068  -0.1061   0.9585   0.0139
  -5.000  -0.0803   0.02424   0.01970  -0.1069   0.9543   0.0167
  -4.500  -0.0069   0.01641   0.01116  -0.1115   0.9488   0.0091
  -4.250   0.0266   0.01456   0.00907  -0.1128   0.9453   0.0086
  -4.000   0.0584   0.01308   0.00739  -0.1136   0.9404   0.0084
  -3.750   0.0903   0.01198   0.00614  -0.1143   0.9361   0.0085
  -3.500   0.1220   0.01117   0.00522  -0.1151   0.9320   0.0088
  -3.250   0.1523   0.01066   0.00462  -0.1157   0.9261   0.0092
  -3.000   0.1843   0.00994   0.00387  -0.1168   0.9210   0.0101
  -2.750   0.2158   0.00949   0.00338  -0.1176   0.9158   0.0100
  -2.500   0.2470   0.00914   0.00299  -0.1184   0.9099   0.0099
  -2.250   0.2780   0.00887   0.00267  -0.1191   0.9045   0.0098
  -2.000   0.3085   0.00864   0.00241  -0.1197   0.8978   0.0097
  -1.750   0.3387   0.00846   0.00219  -0.1202   0.8913   0.0097
  -1.500   0.3686   0.00833   0.00202  -0.1206   0.8845   0.0097
  -1.250   0.3982   0.00823   0.00189  -0.1210   0.8781   0.0098
  -1.000   0.4276   0.00816   0.00178  -0.1212   0.8705   0.0101
  -0.750   0.4562   0.00812   0.00169  -0.1213   0.8585   0.0107
  -0.500   0.4842   0.00810   0.00161  -0.1211   0.8398   0.0124
  -0.250   0.5257   0.00666   0.00169  -0.1255   0.8088   0.6274
   0.000   0.5526   0.00675   0.00176  -0.1250   0.7788   0.6775
   0.250   0.5791   0.00688   0.00196  -0.1244   0.7509   0.7331
   0.500   0.6069   0.00700   0.00198  -0.1243   0.7297   0.7389
   0.750   0.6340   0.00715   0.00202  -0.1241   0.6964   0.7423
   1.000   0.6582   0.00762   0.00210  -0.1232   0.6068   0.7458
   1.250   0.6800   0.00856   0.00239  -0.1223   0.4652   0.7499
   1.500   0.7038   0.00937   0.00268  -0.1218   0.3537   0.7542
   1.750   0.7286   0.00996   0.00294  -0.1215   0.2767   0.7578
   2.000   0.7545   0.01042   0.00317  -0.1213   0.2237   0.7618
   2.250   0.7807   0.01083   0.00339  -0.1211   0.1810   0.7662
   2.500   0.8069   0.01119   0.00363  -0.1210   0.1504   0.7702
   3.000   0.8594   0.01189   0.00411  -0.1206   0.1011   0.7793
   3.250   0.8859   0.01218   0.00435  -0.1204   0.0882   0.7841
   3.500   0.9123   0.01245   0.00462  -0.1202   0.0801   0.7886
   3.750   0.9390   0.01269   0.00488  -0.1201   0.0741   0.7936
   4.000   0.9653   0.01299   0.00516  -0.1198   0.0678   0.7985
   4.250   0.9917   0.01322   0.00545  -0.1196   0.0640   0.8035
   4.500   1.0178   0.01351   0.00574  -0.1194   0.0586   0.8090
   4.750   1.0437   0.01381   0.00606  -0.1191   0.0540   0.8142
   5.000   1.0696   0.01409   0.00638  -0.1188   0.0501   0.8199
   5.500   1.1206   0.01473   0.00708  -0.1181   0.0422   0.8314
   5.750   1.1459   0.01505   0.00746  -0.1177   0.0379   0.8378
   6.000   1.1705   0.01544   0.00787  -0.1172   0.0332   0.8439
   6.250   1.1951   0.01582   0.00829  -0.1167   0.0278   0.8510
   6.500   1.2188   0.01627   0.00877  -0.1160   0.0243   0.8585
   6.750   1.2425   0.01673   0.00930  -0.1153   0.0226   0.8672
   7.000   1.2655   0.01720   0.00984  -0.1145   0.0214   0.8773
   7.250   1.2881   0.01771   0.01044  -0.1136   0.0203   0.8894
   7.500   1.3096   0.01827   0.01110  -0.1125   0.0193   0.9043
   7.750   1.3286   0.01881   0.01178  -0.1108   0.0185   0.9290
   8.000   1.3483   0.01923   0.01232  -0.1093   0.0180   1.0000
   8.250   1.3713   0.01984   0.01302  -0.1087   0.0174   1.0000
   8.500   1.3938   0.02050   0.01377  -0.1079   0.0167   1.0000
   8.750   1.4159   0.02116   0.01453  -0.1071   0.0160   1.0000
   9.000   1.4373   0.02187   0.01535  -0.1063   0.0153   1.0000
   9.250   1.4580   0.02264   0.01621  -0.1053   0.0146   1.0000
   9.500   1.4775   0.02354   0.01720  -0.1041   0.0137   1.0000
   9.750   1.4943   0.02472   0.01851  -0.1026   0.0129   1.0000
  10.000   1.5130   0.02559   0.01951  -0.1013   0.0125   1.0000
  10.250   1.5329   0.02625   0.02029  -0.1002   0.0121   1.0000
  10.500   1.5517   0.02699   0.02116  -0.0990   0.0115   1.0000
  10.750   1.5701   0.02772   0.02204  -0.0978   0.0106   1.0000
  11.000   1.5880   0.02843   0.02285  -0.0965   0.0097   1.0000
  11.250   1.6049   0.02919   0.02366  -0.0951   0.0087   1.0000
  11.500   1.6189   0.03014   0.02474  -0.0932   0.0079   1.0000
  11.750   1.6318   0.03106   0.02580  -0.0911   0.0069   1.0000
  12.000   1.6420   0.03204   0.02686  -0.0887   0.0060   1.0000
  12.250   1.6496   0.03324   0.02815  -0.0860   0.0054   1.0000
  12.500   1.6551   0.03466   0.02970  -0.0832   0.0050   1.0000
  12.750   1.6591   0.03624   0.03143  -0.0804   0.0047   1.0000
  13.000   1.6614   0.03803   0.03338  -0.0776   0.0044   1.0000
  13.250   1.6616   0.04006   0.03556  -0.0749   0.0042   1.0000
  13.500   1.6598   0.04236   0.03804  -0.0724   0.0040   1.0000
  13.750   1.6551   0.04503   0.04088  -0.0700   0.0038   1.0000
  14.000   1.6485   0.04805   0.04409  -0.0680   0.0037   1.0000
  14.250   1.6394   0.05150   0.04773  -0.0664   0.0036   1.0000
  14.500   1.6289   0.05536   0.05180  -0.0654   0.0036   1.0000
  14.750   1.6152   0.05992   0.05657  -0.0651   0.0036   1.0000
  15.000   1.5984   0.06530   0.06216  -0.0657   0.0035   1.0000
  15.250   1.5785   0.07177   0.06883  -0.0675   0.0035   1.0000
  15.500   1.5524   0.08015   0.07744  -0.0713   0.0035   1.0000
  15.750   1.5184   0.09174   0.08926  -0.0781   0.0036   1.0000
  16.000   1.4663   0.10974   0.10756  -0.0892   0.0038   1.0000
  16.250   1.3933   0.13234   0.13044  -0.1015   0.0043   1.0000
  16.500   1.3233   0.15411   0.15239  -0.1139   0.0050   1.0000
  16.750   1.2725   0.17287   0.17125  -0.1255   0.0055   1.0000
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