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KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: KC-135 Winglet (supercritical Whitcomb) (kc135winglet-il)
Reynolds number: 100,000
Max Cl/Cd: 59.24 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-kc135winglet-il-100000-n5.txt
Download as CSV file: xf-kc135winglet-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.4261   0.09134   0.08638  -0.0320   1.0000   0.0458
  -8.000  -0.4299   0.08869   0.08381  -0.0317   1.0000   0.0466
  -7.750  -0.4349   0.08599   0.08121  -0.0316   1.0000   0.0474
  -7.500  -0.4372   0.08286   0.07816  -0.0329   1.0000   0.0483
  -7.250  -0.4389   0.07937   0.07474  -0.0353   1.0000   0.0493
  -7.000  -0.4386   0.07531   0.07071  -0.0394   1.0000   0.0504
  -6.750  -0.4323   0.07091   0.06607  -0.0486   1.0000   0.0536
  -6.500  -0.4214   0.06793   0.06272  -0.0534   1.0000   0.0542
  -6.250  -0.4156   0.06197   0.05692  -0.0532   1.0000   0.0554
  -6.000  -0.4065   0.05847   0.05350  -0.0526   1.0000   0.0567
  -5.750  -0.3935   0.05531   0.05031  -0.0532   1.0000   0.0585
  -5.500  -0.3754   0.05194   0.04681  -0.0552   1.0000   0.0611
  -5.000  -0.2853   0.04009   0.03372  -0.0670   0.9958   0.0291
  -4.750  -0.2474   0.03602   0.02929  -0.0712   0.9938   0.0263
  -4.500  -0.2073   0.03267   0.02545  -0.0749   0.9917   0.0255
  -4.250  -0.1683   0.03014   0.02249  -0.0780   0.9897   0.0263
  -4.000  -0.1293   0.02776   0.01966  -0.0807   0.9881   0.0259
  -3.750  -0.0901   0.02559   0.01700  -0.0830   0.9867   0.0246
  -3.500  -0.0533   0.02387   0.01489  -0.0846   0.9847   0.0238
  -3.250  -0.0185   0.02251   0.01329  -0.0859   0.9821   0.0235
  -3.000   0.0164   0.02132   0.01198  -0.0873   0.9798   0.0234
  -2.750   0.0517   0.02027   0.01086  -0.0889   0.9777   0.0235
  -2.500   0.0884   0.01937   0.00995  -0.0909   0.9760   0.0239
  -2.250   0.1245   0.01868   0.00922  -0.0929   0.9734   0.0246
  -2.000   0.1593   0.01820   0.00864  -0.0946   0.9698   0.0257
  -1.750   0.1956   0.01783   0.00813  -0.0966   0.9666   0.0277
  -1.500   0.2330   0.01753   0.00771  -0.0987   0.9638   0.0327
  -1.250   0.2752   0.01554   0.00818  -0.1026   0.9647   0.6989
  -1.000   0.2934   0.01585   0.00867  -0.0990   0.9593   0.7972
  -0.750   0.3152   0.01593   0.00872  -0.0970   0.9525   0.8287
  -0.500   0.3389   0.01587   0.00865  -0.0952   0.9477   0.8609
  -0.250   0.3657   0.01589   0.00861  -0.0950   0.9407   0.8718
   0.000   0.3991   0.01589   0.00855  -0.0963   0.9362   0.8792
   0.250   0.4353   0.01587   0.00848  -0.0982   0.9330   0.8859
   0.500   0.4620   0.01594   0.00856  -0.0982   0.9255   0.8937
   0.750   0.4974   0.01585   0.00848  -0.0997   0.9205   0.9007
   1.000   0.5283   0.01576   0.00842  -0.1003   0.9114   0.9088
   1.250   0.5635   0.01540   0.00809  -0.1011   0.9004   0.9161
   1.500   0.5971   0.01492   0.00766  -0.1014   0.8845   0.9248
   1.750   0.6286   0.01437   0.00718  -0.1009   0.8649   0.9353
   2.000   0.6577   0.01390   0.00673  -0.1000   0.8409   0.9494
   2.500   0.7195   0.01335   0.00623  -0.0998   0.7857   1.0000
   2.750   0.7506   0.01332   0.00625  -0.1000   0.7508   1.0000
   3.000   0.7812   0.01334   0.00619  -0.1000   0.6973   1.0000
   3.250   0.8092   0.01366   0.00594  -0.0990   0.5667   1.0000
   3.500   0.8278   0.01504   0.00630  -0.0973   0.3943   1.0000
   3.750   0.8483   0.01639   0.00700  -0.0965   0.2777   1.0000
   4.000   0.8718   0.01744   0.00766  -0.0963   0.2083   1.0000
   4.250   0.8966   0.01833   0.00833  -0.0962   0.1700   1.0000
   4.500   0.9213   0.01918   0.00905  -0.0960   0.1471   1.0000
   4.750   0.9461   0.01998   0.00985  -0.0958   0.1306   1.0000
   5.000   0.9706   0.02081   0.01065  -0.0955   0.1185   1.0000
   5.250   0.9947   0.02167   0.01152  -0.0951   0.1100   1.0000
   5.500   1.0187   0.02258   0.01252  -0.0946   0.1032   1.0000
   5.750   1.0424   0.02354   0.01352  -0.0941   0.0970   1.0000
   6.000   1.0665   0.02443   0.01449  -0.0937   0.0884   1.0000
   6.250   1.0897   0.02524   0.01532  -0.0934   0.0790   1.0000
   6.500   1.1137   0.02600   0.01622  -0.0930   0.0709   1.0000
   6.750   1.1363   0.02713   0.01743  -0.0924   0.0656   1.0000
   7.000   1.1594   0.02824   0.01874  -0.0917   0.0600   1.0000
   7.250   1.1806   0.02958   0.02010  -0.0910   0.0557   1.0000
   7.500   1.2039   0.03117   0.02199  -0.0903   0.0515   1.0000
   7.750   1.2261   0.03280   0.02381  -0.0895   0.0482   1.0000
   8.000   1.2466   0.03428   0.02538  -0.0887   0.0455   1.0000
   8.250   1.2667   0.03628   0.02760  -0.0878   0.0430   1.0000
   8.500   1.2862   0.03842   0.03020  -0.0867   0.0406   1.0000
   8.750   1.3035   0.04093   0.03310  -0.0854   0.0390   1.0000
   9.000   1.3181   0.04353   0.03609  -0.0838   0.0377   1.0000
   9.250   1.3300   0.04621   0.03913  -0.0820   0.0366   1.0000
   9.500   1.3390   0.04897   0.04223  -0.0799   0.0358   1.0000
   9.750   1.3451   0.05186   0.04542  -0.0777   0.0350   1.0000
  10.000   1.3477   0.05498   0.04882  -0.0753   0.0344   1.0000
  10.250   1.3432   0.05873   0.05285  -0.0725   0.0337   1.0000
  10.500   1.3277   0.06250   0.05709  -0.0684   0.0332   1.0000
  10.750   1.3068   0.06640   0.06135  -0.0645   0.0329   1.0000
  11.000   1.2836   0.07092   0.06620  -0.0618   0.0328   1.0000
  11.250   1.2589   0.07612   0.07168  -0.0606   0.0327   1.0000
  11.500   1.2327   0.08219   0.07799  -0.0612   0.0328   1.0000
  11.750   1.2061   0.08924   0.08523  -0.0637   0.0330   1.0000
  12.000   1.1797   0.09751   0.09365  -0.0682   0.0333   1.0000
  12.250   1.1538   0.10737   0.10362  -0.0747   0.0337   1.0000
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