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LOCKHEED C-141 BL0 AIRFOIL (c141a-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-141 BL0 AIRFOIL (c141a-il)
Reynolds number: 50,000
Max Cl/Cd: 27.76 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c141a-il-50000-n5.txt
Download as CSV file: xf-c141a-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL0 AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6836   0.07965   0.07140  -0.0633   1.0000   0.0683
 -11.250  -0.7130   0.07508   0.06676  -0.0629   1.0000   0.0681
 -11.000  -0.7426   0.07148   0.06308  -0.0605   1.0000   0.0680
 -10.750  -0.7724   0.06867   0.06020  -0.0561   1.0000   0.0679
 -10.500  -0.7995   0.06579   0.05717  -0.0514   1.0000   0.0680
 -10.250  -0.8232   0.06272   0.05385  -0.0467   1.0000   0.0683
 -10.000  -0.8317   0.06018   0.05121  -0.0432   1.0000   0.0690
  -9.750  -0.8350   0.05796   0.04887  -0.0400   1.0000   0.0699
  -9.500  -0.8351   0.05599   0.04680  -0.0370   1.0000   0.0713
  -9.250  -0.8370   0.05382   0.04444  -0.0338   1.0000   0.0730
  -9.000  -0.8393   0.05139   0.04171  -0.0303   1.0000   0.0749
  -8.750  -0.8404   0.04874   0.03864  -0.0269   1.0000   0.0769
  -8.500  -0.8389   0.04602   0.03538  -0.0235   1.0000   0.0788
  -8.250  -0.8269   0.04434   0.03370  -0.0216   1.0000   0.0811
  -8.000  -0.8150   0.04282   0.03203  -0.0196   1.0000   0.0842
  -7.750  -0.8029   0.04099   0.02989  -0.0174   1.0000   0.0877
  -7.500  -0.7890   0.03909   0.02756  -0.0153   1.0000   0.0912
  -7.250  -0.7724   0.03782   0.02634  -0.0139   1.0000   0.0949
  -7.000  -0.7552   0.03649   0.02481  -0.0123   1.0000   0.0996
  -6.750  -0.7364   0.03510   0.02314  -0.0109   1.0000   0.1046
  -6.500  -0.7177   0.03404   0.02213  -0.0096   1.0000   0.1100
  -6.250  -0.6973   0.03296   0.02082  -0.0083   1.0000   0.1167
  -6.000  -0.6774   0.03197   0.01988  -0.0071   1.0000   0.1234
  -5.750  -0.6565   0.03110   0.01883  -0.0059   1.0000   0.1320
  -5.500  -0.6370   0.03023   0.01805  -0.0046   1.0000   0.1409
  -5.250  -0.6171   0.02942   0.01719  -0.0034   1.0000   0.1520
  -5.000  -0.5977   0.02866   0.01641  -0.0020   1.0000   0.1655
  -4.750  -0.5789   0.02787   0.01568  -0.0007   1.0000   0.1819
  -4.500  -0.5606   0.02706   0.01499   0.0006   1.0000   0.2033
  -4.250  -0.5425   0.02622   0.01430   0.0019   1.0000   0.2331
  -4.000  -0.5250   0.02527   0.01367   0.0031   1.0000   0.2802
  -3.750  -0.5104   0.02417   0.01316   0.0050   1.0000   0.3625
  -3.500  -0.4976   0.02325   0.01311   0.0079   1.0000   0.5000
  -3.250  -0.4822   0.02304   0.01341   0.0114   1.0000   0.6218
  -3.000  -0.4654   0.02312   0.01362   0.0144   1.0000   0.6999
  -2.750  -0.4474   0.02329   0.01381   0.0172   1.0000   0.7559
  -2.500  -0.4256   0.02359   0.01411   0.0195   1.0000   0.8021
  -2.250  -0.3992   0.02402   0.01449   0.0208   1.0000   0.8439
  -2.000  -0.3642   0.02461   0.01498   0.0204   1.0000   0.8827
  -1.750  -0.3140   0.02548   0.01568   0.0170   1.0000   0.9216
  -1.500  -0.2410   0.02649   0.01646   0.0087   1.0000   0.9544
  -1.250  -0.1824   0.02691   0.01669   0.0020   1.0000   0.9732
  -1.000  -0.1353   0.02708   0.01673  -0.0030   1.0000   0.9876
  -0.750  -0.0898   0.02723   0.01675  -0.0080   0.9991   1.0000
  -0.500  -0.0582   0.02725   0.01669  -0.0103   0.9918   1.0000
  -0.250  -0.0275   0.02731   0.01668  -0.0124   0.9842   1.0000
   0.000   0.0008   0.02736   0.01667  -0.0140   0.9758   1.0000
   0.250   0.0296   0.02747   0.01673  -0.0155   0.9679   1.0000
   0.500   0.0583   0.02760   0.01683  -0.0169   0.9595   1.0000
   0.750   0.0835   0.02771   0.01691  -0.0175   0.9502   1.0000
   1.000   0.1161   0.02794   0.01712  -0.0194   0.9428   1.0000
   1.250   0.1382   0.02805   0.01723  -0.0193   0.9321   1.0000
   1.500   0.1669   0.02825   0.01744  -0.0203   0.9233   1.0000
   1.750   0.1954   0.02844   0.01765  -0.0212   0.9137   1.0000
   2.000   0.2193   0.02861   0.01785  -0.0211   0.9028   1.0000
   2.250   0.2558   0.02882   0.01811  -0.0232   0.8947   1.0000
   2.500   0.2790   0.02895   0.01830  -0.0228   0.8821   1.0000
   2.750   0.3047   0.02906   0.01848  -0.0228   0.8693   1.0000
   3.000   0.3356   0.02906   0.01857  -0.0234   0.8559   1.0000
   3.250   0.3699   0.02885   0.01847  -0.0242   0.8398   1.0000
   3.500   0.4052   0.02839   0.01814  -0.0248   0.8206   1.0000
   3.750   0.4457   0.02763   0.01755  -0.0258   0.8003   1.0000
   4.000   0.4731   0.02700   0.01705  -0.0246   0.7773   1.0000
   4.250   0.5035   0.02619   0.01638  -0.0235   0.7532   1.0000
   4.500   0.5276   0.02554   0.01586  -0.0214   0.7253   1.0000
   4.750   0.5571   0.02478   0.01522  -0.0201   0.6915   1.0000
   5.000   0.5890   0.02407   0.01457  -0.0190   0.6445   1.0000
   5.250   0.6298   0.02340   0.01375  -0.0191   0.5608   1.0000
   5.500   0.6569   0.02366   0.01331  -0.0175   0.4364   1.0000
   5.750   0.6627   0.02470   0.01369  -0.0134   0.3472   1.0000
   6.000   0.6675   0.02586   0.01438  -0.0096   0.2879   1.0000
   6.250   0.6753   0.02697   0.01516  -0.0065   0.2471   1.0000
   6.500   0.6859   0.02807   0.01599  -0.0039   0.2171   1.0000
   6.750   0.7006   0.02909   0.01690  -0.0019   0.1930   1.0000
   7.000   0.7173   0.03014   0.01783  -0.0003   0.1738   1.0000
   7.250   0.7375   0.03119   0.01884   0.0007   0.1580   1.0000
   7.500   0.7614   0.03227   0.01991   0.0012   0.1441   1.0000
   7.750   0.7883   0.03341   0.02107   0.0012   0.1322   1.0000
   8.000   0.8150   0.03464   0.02225   0.0012   0.1226   1.0000
   8.250   0.8407   0.03587   0.02361   0.0014   0.1136   1.0000
   8.500   0.8679   0.03733   0.02514   0.0013   0.1065   1.0000
   8.750   0.8907   0.03873   0.02667   0.0018   0.1000   1.0000
   9.000   0.9150   0.04039   0.02838   0.0021   0.0950   1.0000
   9.250   0.9345   0.04217   0.03046   0.0031   0.0900   1.0000
   9.500   0.9526   0.04372   0.03206   0.0041   0.0860   1.0000
   9.750   0.9693   0.04584   0.03441   0.0053   0.0828   1.0000
  10.000   0.9795   0.04812   0.03707   0.0075   0.0796   1.0000
  10.250   0.9890   0.05011   0.03928   0.0095   0.0767   1.0000
  10.500   1.0007   0.05196   0.04119   0.0111   0.0743   1.0000
  10.750   1.0062   0.05451   0.04397   0.0133   0.0727   1.0000
  11.000   0.9978   0.05742   0.04731   0.0172   0.0714   1.0000
  11.250   0.9855   0.06034   0.05059   0.0211   0.0702   1.0000
  11.500   0.9709   0.06343   0.05398   0.0245   0.0692   1.0000
  11.750   0.9542   0.06679   0.05760   0.0274   0.0684   1.0000
  12.000   0.9343   0.07058   0.06163   0.0296   0.0678   1.0000
  12.250   0.9097   0.07509   0.06638   0.0309   0.0675   1.0000
  12.500   0.8774   0.08096   0.07248   0.0306   0.0677   1.0000
  12.750   0.8356   0.08919   0.08091   0.0277   0.0685   1.0000
  13.000   0.7897   0.10044   0.09229   0.0213   0.0697   1.0000
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