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KC-135 BL200.76 AIRFOIL (kc135c-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: KC-135 BL200.76 AIRFOIL (kc135c-il)
Reynolds number: 100,000
Max Cl/Cd: 52.04 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-kc135c-il-100000.txt
Download as CSV file: xf-kc135c-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: KC-135 BL200.76 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.3755   0.10574   0.10098  -0.0259   1.0000   0.0770
 -10.250  -0.3827   0.10207   0.09735  -0.0284   1.0000   0.0792
 -10.000  -0.4712   0.10482   0.09977  -0.0254   1.0000   0.0715
  -9.750  -0.4688   0.10127   0.09625  -0.0265   1.0000   0.0739
  -9.500  -0.4711   0.09751   0.09254  -0.0288   1.0000   0.0771
  -9.250  -0.4786   0.09341   0.08852  -0.0327   1.0000   0.0789
  -9.000  -0.4928   0.08886   0.08404  -0.0380   1.0000   0.0797
  -8.750  -0.5075   0.08540   0.08060  -0.0399   1.0000   0.0799
  -8.500  -0.5317   0.08326   0.07839  -0.0402   1.0000   0.0805
  -8.250  -0.5506   0.08168   0.07664  -0.0394   1.0000   0.0809
  -8.000  -0.5237   0.07402   0.06929  -0.0389   1.0000   0.0848
  -7.750  -0.5234   0.07095   0.06622  -0.0378   1.0000   0.0877
  -7.500  -0.5293   0.06813   0.06335  -0.0367   1.0000   0.0909
  -7.250  -0.5497   0.06785   0.06272  -0.0341   1.0000   0.0951
  -7.000  -0.5541   0.06367   0.05852  -0.0321   1.0000   0.0971
  -6.750  -0.5460   0.05978   0.05483  -0.0302   1.0000   0.1006
  -6.500  -0.5499   0.05779   0.05278  -0.0270   1.0000   0.1057
  -6.250  -0.5666   0.05730   0.05187  -0.0224   1.0000   0.1115
  -6.000  -0.5609   0.05341   0.04820  -0.0205   1.0000   0.1152
  -5.750  -0.5686   0.05286   0.04724  -0.0167   1.0000   0.1262
  -5.500  -0.5468   0.03785   0.03303  -0.0141   1.0000   0.1305
  -5.250  -0.5473   0.03551   0.03050  -0.0119   1.0000   0.1431
  -5.000  -0.5563   0.04463   0.03900  -0.0103   1.0000   0.1598
  -4.500  -0.5484   0.04133   0.03538  -0.0058   1.0000   0.2133
  -4.250  -0.5317   0.03786   0.03219  -0.0056   0.9970   0.2531
  -4.000  -0.5077   0.03504   0.02938  -0.0063   0.9916   0.2967
  -3.750  -0.4748   0.03257   0.02656  -0.0081   0.9859   0.3133
  -3.500  -0.4313   0.02979   0.02318  -0.0106   0.9810   0.2801
  -3.250  -0.3521   0.02961   0.02077  -0.0106   0.9760   0.0946
  -3.000  -0.3140   0.02718   0.01814  -0.0121   0.9720   0.0874
  -2.750  -0.2783   0.02625   0.01673  -0.0126   0.9665   0.0824
  -2.500  -0.2433   0.02506   0.01539  -0.0136   0.9613   0.0802
  -2.250  -0.2039   0.02380   0.01405  -0.0155   0.9573   0.0803
  -2.000  -0.1747   0.02256   0.01292  -0.0160   0.9517   0.0852
  -1.750  -0.1442   0.02174   0.01218  -0.0165   0.9459   0.0901
  -1.500  -0.1081   0.02114   0.01153  -0.0181   0.9415   0.0964
  -1.250  -0.0890   0.02066   0.01103  -0.0169   0.9336   0.1093
  -1.000  -0.0556   0.01997   0.01042  -0.0181   0.9285   0.1445
  -0.750  -0.0118   0.01835   0.01179  -0.0158   0.9291   0.9381
  -0.500   0.1941   0.01917   0.01207  -0.0474   0.9455   1.0000
  -0.250   0.2272   0.01912   0.01193  -0.0499   0.9380   1.0000
   0.000   0.2590   0.01907   0.01182  -0.0520   0.9301   1.0000
   0.250   0.2862   0.01908   0.01179  -0.0533   0.9217   1.0000
   0.500   0.3237   0.01902   0.01168  -0.0562   0.9149   1.0000
   0.750   0.3450   0.01910   0.01175  -0.0562   0.9053   1.0000
   1.000   0.3886   0.01894   0.01158  -0.0597   0.8989   1.0000
   1.250   0.4166   0.01879   0.01143  -0.0601   0.8865   1.0000
   1.500   0.4566   0.01827   0.01094  -0.0618   0.8726   1.0000
   1.750   0.4865   0.01787   0.01054  -0.0616   0.8582   1.0000
   2.000   0.5060   0.01780   0.01049  -0.0600   0.8461   1.0000
   2.250   0.5282   0.01775   0.01045  -0.0588   0.8358   1.0000
   2.500   0.5510   0.01767   0.01040  -0.0576   0.8255   1.0000
   2.750   0.5666   0.01779   0.01057  -0.0553   0.8130   1.0000
   3.000   0.5847   0.01784   0.01067  -0.0532   0.8007   1.0000
   3.250   0.6049   0.01783   0.01071  -0.0513   0.7882   1.0000
   3.500   0.6263   0.01774   0.01067  -0.0494   0.7750   1.0000
   3.750   0.6482   0.01759   0.01062  -0.0475   0.7610   1.0000
   4.000   0.6701   0.01739   0.01049  -0.0455   0.7456   1.0000
   4.250   0.6928   0.01712   0.01029  -0.0436   0.7289   1.0000
   4.500   0.7170   0.01674   0.00997  -0.0416   0.7107   1.0000
   4.750   0.7377   0.01648   0.00982  -0.0393   0.6884   1.0000
   5.000   0.7598   0.01613   0.00952  -0.0370   0.6626   1.0000
   5.250   0.7786   0.01585   0.00931  -0.0342   0.6286   1.0000
   5.500   0.7965   0.01553   0.00893  -0.0311   0.5792   1.0000
   5.750   0.8092   0.01555   0.00871  -0.0274   0.5007   1.0000
   6.000   0.8194   0.01618   0.00879  -0.0237   0.4183   1.0000
   6.250   0.8310   0.01707   0.00931  -0.0208   0.3612   1.0000
   6.500   0.8438   0.01795   0.00996  -0.0183   0.3160   1.0000
   6.750   0.8560   0.01883   0.01067  -0.0159   0.2708   1.0000
   7.000   0.8641   0.01995   0.01152  -0.0128   0.2099   1.0000
   7.250   0.8651   0.02188   0.01279  -0.0088   0.1257   1.0000
   7.500   0.8738   0.02356   0.01419  -0.0058   0.0997   1.0000
   7.750   0.8863   0.02508   0.01559  -0.0036   0.0859   1.0000
   8.000   0.9037   0.02663   0.01716  -0.0019   0.0769   1.0000
   8.250   0.9257   0.02870   0.01914  -0.0011   0.0703   1.0000
   8.500   0.9470   0.03028   0.02088  -0.0001   0.0641   1.0000
   8.750   0.9771   0.03350   0.02401  -0.0008   0.0598   1.0000
   9.000   0.9982   0.03574   0.02667   0.0005   0.0580   1.0000
   9.250   1.0148   0.03800   0.02932   0.0021   0.0555   1.0000
   9.500   1.0293   0.04044   0.03206   0.0038   0.0531   1.0000
   9.750   1.0402   0.04353   0.03555   0.0058   0.0527   1.0000
  10.000   1.0442   0.04701   0.03950   0.0085   0.0528   1.0000
  10.250   1.0413   0.05079   0.04376   0.0116   0.0537   1.0000
  10.500   1.0327   0.05470   0.04812   0.0148   0.0546   1.0000
  10.750   1.0201   0.05845   0.05220   0.0180   0.0557   1.0000
  11.000   1.0036   0.06201   0.05599   0.0213   0.0566   1.0000
  11.250   0.9863   0.06581   0.05999   0.0236   0.0574   1.0000
  11.500   0.9696   0.06996   0.06430   0.0248   0.0582   1.0000
  11.750   0.9583   0.07510   0.06952   0.0251   0.0593   1.0000
  12.000   0.8313   0.07224   0.06715   0.0273   0.0584   1.0000
  12.250   0.8068   0.07858   0.07360   0.0255   0.0590   1.0000
  12.500   0.7980   0.08486   0.07994   0.0244   0.0601   1.0000
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