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KC-135 BL52.44 AIRFOIL (kc135a-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: KC-135 BL52.44 AIRFOIL (kc135a-il)
Reynolds number: 200,000
Max Cl/Cd: 62.1 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-kc135a-il-200000-n5.txt
Download as CSV file: xf-kc135a-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: KC-135 BL52.44 AIRFOIL                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.5931   0.09563   0.09154  -0.0411   1.0000   0.0216
 -13.500  -0.6141   0.08718   0.08302  -0.0464   1.0000   0.0213
 -13.250  -0.6478   0.07779   0.07349  -0.0523   1.0000   0.0212
 -13.000  -0.6721   0.07125   0.06682  -0.0558   1.0000   0.0210
 -12.750  -0.7030   0.06455   0.05991  -0.0587   1.0000   0.0210
 -12.500  -0.7248   0.05966   0.05484  -0.0600   1.0000   0.0209
 -12.250  -0.7461   0.05523   0.05021  -0.0603   1.0000   0.0209
 -12.000  -0.7682   0.05106   0.04579  -0.0595   1.0000   0.0210
 -11.750  -0.7856   0.04762   0.04211  -0.0577   1.0000   0.0211
 -11.500  -0.8010   0.04454   0.03875  -0.0551   1.0000   0.0212
 -11.250  -0.8131   0.04183   0.03577  -0.0517   1.0000   0.0213
 -11.000  -0.8218   0.03949   0.03316  -0.0479   1.0000   0.0214
 -10.750  -0.8282   0.03730   0.03068  -0.0438   1.0000   0.0216
 -10.500  -0.8252   0.03556   0.02877  -0.0409   1.0000   0.0218
 -10.250  -0.8177   0.03446   0.02762  -0.0384   1.0000   0.0220
 -10.000  -0.8095   0.03344   0.02654  -0.0359   1.0000   0.0223
  -9.750  -0.8012   0.03249   0.02552  -0.0333   1.0000   0.0227
  -9.500  -0.7865   0.03143   0.02438  -0.0320   0.9970   0.0232
  -9.250  -0.7571   0.02971   0.02245  -0.0334   0.9845   0.0239
  -9.000  -0.7252   0.02787   0.02036  -0.0351   0.9732   0.0247
  -8.750  -0.6911   0.02618   0.01841  -0.0369   0.9602   0.0254
  -8.500  -0.6558   0.02477   0.01691  -0.0391   0.9451   0.0260
  -8.250  -0.6199   0.02370   0.01580  -0.0414   0.9278   0.0269
  -8.000  -0.5844   0.02263   0.01464  -0.0435   0.9081   0.0278
  -7.750  -0.5519   0.02165   0.01353  -0.0449   0.8868   0.0290
  -7.500  -0.5238   0.02079   0.01250  -0.0453   0.8654   0.0303
  -7.250  -0.5003   0.02017   0.01186  -0.0449   0.8452   0.0317
  -7.000  -0.4789   0.01962   0.01122  -0.0440   0.8274   0.0333
  -6.750  -0.4589   0.01908   0.01053  -0.0428   0.8121   0.0350
  -6.500  -0.4409   0.01849   0.00987  -0.0412   0.7987   0.0362
  -6.250  -0.4221   0.01802   0.00934  -0.0398   0.7869   0.0380
  -6.000  -0.4025   0.01762   0.00885  -0.0384   0.7758   0.0405
  -5.750  -0.3840   0.01714   0.00830  -0.0369   0.7661   0.0428
  -5.500  -0.3643   0.01673   0.00785  -0.0355   0.7572   0.0454
  -5.250  -0.3435   0.01639   0.00741  -0.0343   0.7492   0.0487
  -5.000  -0.3243   0.01593   0.00692  -0.0329   0.7413   0.0518
  -4.750  -0.3029   0.01561   0.00651  -0.0318   0.7343   0.0562
  -4.500  -0.2821   0.01523   0.00610  -0.0306   0.7266   0.0611
  -4.250  -0.2600   0.01494   0.00572  -0.0296   0.7200   0.0680
  -4.000  -0.2384   0.01456   0.00538  -0.0285   0.7132   0.0803
  -3.750  -0.2184   0.01407   0.00501  -0.0272   0.7069   0.1156
  -3.250  -0.2008   0.01187   0.00440  -0.0211   0.6955   0.4975
  -3.000  -0.1769   0.01184   0.00440  -0.0201   0.6895   0.5323
  -2.750  -0.1519   0.01188   0.00436  -0.0194   0.6844   0.5562
  -2.500  -0.1271   0.01189   0.00439  -0.0186   0.6782   0.5766
  -2.250  -0.1018   0.01192   0.00439  -0.0180   0.6725   0.5938
  -2.000  -0.0761   0.01197   0.00436  -0.0174   0.6679   0.6084
  -1.750  -0.0500   0.01196   0.00438  -0.0169   0.6628   0.6201
  -1.500  -0.0235   0.01196   0.00433  -0.0166   0.6574   0.6284
  -1.250   0.0039   0.01193   0.00426  -0.0164   0.6524   0.6333
  -1.000   0.0312   0.01193   0.00419  -0.0163   0.6477   0.6384
  -0.750   0.0582   0.01192   0.00415  -0.0161   0.6423   0.6436
  -0.500   0.0856   0.01190   0.00411  -0.0160   0.6374   0.6479
  -0.250   0.1130   0.01189   0.00408  -0.0159   0.6330   0.6530
   0.000   0.1400   0.01190   0.00407  -0.0157   0.6277   0.6589
   0.250   0.1670   0.01190   0.00407  -0.0156   0.6223   0.6642
   0.500   0.1942   0.01189   0.00406  -0.0154   0.6174   0.6693
   0.750   0.2213   0.01190   0.00406  -0.0152   0.6124   0.6756
   1.000   0.2480   0.01191   0.00410  -0.0150   0.6067   0.6819
   1.250   0.2749   0.01191   0.00412  -0.0148   0.6017   0.6882
   1.500   0.3021   0.01194   0.00413  -0.0147   0.5971   0.6952
   1.750   0.3285   0.01195   0.00421  -0.0144   0.5910   0.7022
   2.000   0.3548   0.01194   0.00422  -0.0140   0.5838   0.7104
   2.250   0.3806   0.01192   0.00424  -0.0136   0.5746   0.7189
   2.500   0.4066   0.01191   0.00424  -0.0131   0.5661   0.7283
   2.750   0.4325   0.01192   0.00433  -0.0127   0.5586   0.7383
   3.000   0.4585   0.01194   0.00439  -0.0123   0.5515   0.7502
   3.250   0.4845   0.01196   0.00449  -0.0119   0.5444   0.7629
   3.500   0.5103   0.01198   0.00460  -0.0115   0.5367   0.7772
   3.750   0.5365   0.01201   0.00470  -0.0111   0.5293   0.7934
   4.000   0.5630   0.01205   0.00485  -0.0108   0.5207   0.8121
   4.250   0.5906   0.01210   0.00499  -0.0107   0.5119   0.8333
   4.500   0.6198   0.01217   0.00515  -0.0109   0.5018   0.8563
   4.750   0.6519   0.01227   0.00534  -0.0118   0.4902   0.8785
   5.000   0.6864   0.01240   0.00554  -0.0132   0.4771   0.8996
   5.250   0.7222   0.01256   0.00573  -0.0150   0.4613   0.9190
   5.500   0.7576   0.01275   0.00595  -0.0167   0.4423   0.9360
   5.750   0.7911   0.01298   0.00615  -0.0181   0.4182   0.9509
   6.000   0.8234   0.01330   0.00639  -0.0194   0.3870   0.9641
   6.250   0.8539   0.01375   0.00671  -0.0205   0.3542   0.9768
   6.500   0.8839   0.01430   0.00712  -0.0216   0.3226   0.9887
   6.750   0.9150   0.01491   0.00761  -0.0232   0.2932   0.9993
   7.000   0.9275   0.01539   0.00800  -0.0207   0.2746   1.0000
   7.250   0.9385   0.01585   0.00840  -0.0179   0.2586   1.0000
   7.750   0.9608   0.01681   0.00926  -0.0125   0.2305   1.0000
   8.000   0.9710   0.01731   0.00972  -0.0097   0.2170   1.0000
   8.250   0.9798   0.01785   0.01021  -0.0067   0.2028   1.0000
   8.500   0.9876   0.01841   0.01072  -0.0035   0.1898   1.0000
   8.750   0.9926   0.01896   0.01123   0.0001   0.1781   1.0000
   9.000   0.9987   0.01955   0.01178   0.0033   0.1675   1.0000
   9.250   1.0077   0.02013   0.01237   0.0060   0.1579   1.0000
   9.500   1.0155   0.02082   0.01305   0.0086   0.1490   1.0000
   9.750   1.0241   0.02156   0.01379   0.0109   0.1396   1.0000
  10.000   1.0335   0.02233   0.01458   0.0129   0.1311   1.0000
  10.250   1.0412   0.02326   0.01550   0.0149   0.1231   1.0000
  10.500   1.0503   0.02419   0.01645   0.0166   0.1140   1.0000
  10.750   1.0587   0.02522   0.01750   0.0182   0.1063   1.0000
  11.000   1.0655   0.02643   0.01870   0.0197   0.0982   1.0000
  11.250   1.0739   0.02760   0.01990   0.0210   0.0901   1.0000
  11.500   1.0807   0.02894   0.02125   0.0222   0.0820   1.0000
  11.750   1.0864   0.03042   0.02273   0.0233   0.0748   1.0000
  12.000   1.0915   0.03201   0.02432   0.0244   0.0671   1.0000
  12.250   1.0972   0.03361   0.02596   0.0253   0.0607   1.0000
  12.500   1.1012   0.03539   0.02777   0.0261   0.0558   1.0000
  12.750   1.1048   0.03727   0.02967   0.0268   0.0514   1.0000
  13.000   1.1078   0.03924   0.03169   0.0275   0.0484   1.0000
  13.250   1.1108   0.04127   0.03378   0.0280   0.0453   1.0000
  13.500   1.1110   0.04360   0.03614   0.0284   0.0431   1.0000
  13.750   1.1134   0.04579   0.03843   0.0287   0.0412   1.0000
  14.000   1.1149   0.04813   0.04085   0.0289   0.0393   1.0000
  14.250   1.1150   0.05069   0.04347   0.0289   0.0380   1.0000
  14.500   1.1127   0.05359   0.04641   0.0288   0.0366   1.0000
  14.750   1.1135   0.05624   0.04918   0.0286   0.0355   1.0000
  15.000   1.1136   0.05905   0.05209   0.0283   0.0344   1.0000
  15.250   1.1128   0.06206   0.05518   0.0278   0.0332   1.0000
  15.500   1.1105   0.06531   0.05851   0.0271   0.0323   1.0000
  15.750   1.1067   0.06882   0.06207   0.0263   0.0316   1.0000
  16.000   1.1046   0.07220   0.06555   0.0255   0.0309   1.0000
  16.250   1.1033   0.07556   0.06905   0.0246   0.0301   1.0000
  16.500   1.1015   0.07907   0.07266   0.0236   0.0293   1.0000
  16.750   1.0987   0.08277   0.07646   0.0224   0.0287   1.0000
  17.000   1.0951   0.08668   0.08046   0.0210   0.0280   1.0000
  17.250   1.0915   0.09065   0.08452   0.0195   0.0275   1.0000
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