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LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il)
Reynolds number: 500,000
Max Cl/Cd: 70.05 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c141f-il-500000-n5.txt
Download as CSV file: xf-c141f-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL958.89 AIRFOIL                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.4897   0.09881   0.09617  -0.0326   1.0000   0.0185
 -10.000  -0.4910   0.09528   0.09266  -0.0338   0.9996   0.0188
  -9.500  -0.6984   0.02733   0.02278  -0.0761   0.9787   0.0227
  -9.250  -0.6843   0.02320   0.01796  -0.0760   0.9765   0.0234
  -9.000  -0.6595   0.02164   0.01614  -0.0764   0.9754   0.0238
  -8.750  -0.6310   0.02094   0.01538  -0.0771   0.9745   0.0241
  -8.500  -0.6013   0.02033   0.01472  -0.0779   0.9737   0.0243
  -8.250  -0.5713   0.01972   0.01403  -0.0788   0.9731   0.0247
  -8.000  -0.5463   0.01914   0.01336  -0.0785   0.9711   0.0251
  -7.750  -0.5235   0.01850   0.01261  -0.0777   0.9682   0.0256
  -7.500  -0.4969   0.01771   0.01165  -0.0778   0.9662   0.0262
  -7.250  -0.4691   0.01689   0.01066  -0.0780   0.9646   0.0268
  -7.000  -0.4402   0.01620   0.00986  -0.0784   0.9632   0.0272
  -6.750  -0.4104   0.01572   0.00937  -0.0791   0.9620   0.0276
  -6.500  -0.3800   0.01530   0.00893  -0.0797   0.9609   0.0280
  -6.250  -0.3494   0.01487   0.00846  -0.0804   0.9598   0.0285
  -6.000  -0.3245   0.01450   0.00803  -0.0798   0.9570   0.0291
  -5.750  -0.2996   0.01411   0.00758  -0.0792   0.9536   0.0298
  -5.500  -0.2718   0.01370   0.00709  -0.0791   0.9512   0.0305
  -5.250  -0.2433   0.01326   0.00664  -0.0793   0.9491   0.0311
  -5.000  -0.2138   0.01292   0.00630  -0.0797   0.9473   0.0317
  -4.750  -0.1838   0.01259   0.00597  -0.0801   0.9456   0.0324
  -4.500  -0.1561   0.01228   0.00564  -0.0800   0.9432   0.0332
  -4.250  -0.1322   0.01201   0.00535  -0.0791   0.9388   0.0340
  -4.000  -0.1052   0.01171   0.00503  -0.0788   0.9355   0.0349
  -3.750  -0.0768   0.01141   0.00476  -0.0788   0.9328   0.0359
  -3.500  -0.0475   0.01114   0.00449  -0.0790   0.9304   0.0369
  -3.250  -0.0192   0.01088   0.00423  -0.0790   0.9278   0.0380
  -3.000   0.0050   0.01068   0.00402  -0.0781   0.9222   0.0389
  -2.750   0.0323   0.01038   0.00375  -0.0778   0.9171   0.0402
  -2.500   0.0615   0.01011   0.00349  -0.0779   0.9127   0.0417
  -2.250   0.0862   0.00994   0.00333  -0.0770   0.9049   0.0433
  -2.000   0.1137   0.00970   0.00310  -0.0768   0.8986   0.0448
  -1.750   0.1401   0.00949   0.00293  -0.0763   0.8899   0.0466
  -1.500   0.1681   0.00930   0.00273  -0.0761   0.8820   0.0488
  -1.250   0.1953   0.00911   0.00258  -0.0758   0.8723   0.0515
  -1.000   0.2239   0.00893   0.00239  -0.0756   0.8611   0.0547
  -0.750   0.2526   0.00876   0.00221  -0.0755   0.8468   0.0588
  -0.500   0.2809   0.00864   0.00206  -0.0754   0.8311   0.0650
  -0.250   0.3087   0.00857   0.00197  -0.0751   0.8150   0.0735
   0.000   0.3356   0.00853   0.00191  -0.0747   0.7945   0.0849
   0.250   0.3616   0.00853   0.00185  -0.0741   0.7651   0.0989
   0.500   0.3862   0.00859   0.00181  -0.0731   0.7266   0.1174
   0.750   0.4096   0.00866   0.00180  -0.0721   0.6808   0.1555
   1.000   0.4247   0.00741   0.00185  -0.0702   0.6362   0.6523
   1.250   0.4428   0.00742   0.00197  -0.0679   0.5760   0.7608
   1.500   0.4583   0.00767   0.00218  -0.0650   0.4985   0.8535
   1.750   0.4755   0.00818   0.00243  -0.0624   0.4061   0.9213
   2.000   0.5065   0.00891   0.00274  -0.0632   0.3044   0.9722
   2.250   0.5448   0.00936   0.00293  -0.0657   0.2554   0.9898
   2.500   0.5844   0.00970   0.00310  -0.0684   0.2267   0.9987
   3.000   0.6322   0.01010   0.00332  -0.0668   0.1989   1.0000
   3.250   0.6549   0.01029   0.00345  -0.0657   0.1886   1.0000
   3.500   0.6778   0.01048   0.00358  -0.0646   0.1778   1.0000
   3.750   0.7013   0.01067   0.00371  -0.0637   0.1672   1.0000
   4.000   0.7247   0.01089   0.00387  -0.0627   0.1544   1.0000
   4.250   0.7480   0.01115   0.00403  -0.0618   0.1375   1.0000
   4.500   0.7708   0.01147   0.00422  -0.0608   0.1173   1.0000
   4.750   0.7939   0.01179   0.00444  -0.0599   0.1034   1.0000
   5.000   0.8173   0.01209   0.00468  -0.0590   0.0951   1.0000
   5.250   0.8413   0.01235   0.00491  -0.0582   0.0904   1.0000
   5.500   0.8649   0.01265   0.00517  -0.0574   0.0863   1.0000
   5.750   0.8889   0.01293   0.00544  -0.0566   0.0831   1.0000
   6.000   0.9127   0.01321   0.00571  -0.0559   0.0796   1.0000
   6.250   0.9359   0.01355   0.00601  -0.0550   0.0760   1.0000
   6.500   0.9599   0.01382   0.00629  -0.0543   0.0734   1.0000
   6.750   0.9836   0.01411   0.00658  -0.0535   0.0709   1.0000
   7.000   1.0067   0.01444   0.00689  -0.0527   0.0682   1.0000
   7.250   1.0299   0.01477   0.00722  -0.0519   0.0660   1.0000
   7.500   1.0535   0.01504   0.00753  -0.0511   0.0637   1.0000
   7.750   1.0766   0.01537   0.00784  -0.0503   0.0613   1.0000
   8.000   1.0990   0.01573   0.00821  -0.0494   0.0590   1.0000
   8.250   1.1222   0.01602   0.00853  -0.0486   0.0568   1.0000
   8.500   1.1449   0.01635   0.00887  -0.0477   0.0543   1.0000
   8.750   1.1671   0.01670   0.00923  -0.0468   0.0518   1.0000
   9.000   1.1894   0.01702   0.00958  -0.0459   0.0485   1.0000
   9.250   1.2111   0.01739   0.00995  -0.0449   0.0450   1.0000
   9.500   1.2321   0.01778   0.01034  -0.0438   0.0408   1.0000
   9.750   1.2517   0.01822   0.01076  -0.0424   0.0366   1.0000
  10.000   1.2705   0.01872   0.01125  -0.0410   0.0330   1.0000
  10.250   1.2888   0.01925   0.01180  -0.0395   0.0303   1.0000
  10.500   1.3065   0.01983   0.01240  -0.0379   0.0282   1.0000
  10.750   1.3240   0.02042   0.01302  -0.0363   0.0264   1.0000
  11.000   1.3406   0.02109   0.01371  -0.0347   0.0250   1.0000
  11.250   1.3576   0.02170   0.01438  -0.0331   0.0239   1.0000
  11.500   1.3736   0.02238   0.01511  -0.0314   0.0228   1.0000
  12.000   1.4038   0.02385   0.01669  -0.0280   0.0211   1.0000
  12.250   1.4184   0.02461   0.01751  -0.0263   0.0204   1.0000
  12.500   1.4321   0.02543   0.01840  -0.0245   0.0197   1.0000
  12.750   1.4444   0.02636   0.01938  -0.0226   0.0192   1.0000
  13.000   1.4553   0.02738   0.02046  -0.0206   0.0187   1.0000
  13.250   1.4671   0.02833   0.02150  -0.0188   0.0184   1.0000
  13.500   1.4778   0.02936   0.02263  -0.0170   0.0180   1.0000
  13.750   1.4876   0.03048   0.02384  -0.0151   0.0176   1.0000
  14.000   1.4964   0.03170   0.02514  -0.0133   0.0173   1.0000
  14.250   1.5040   0.03302   0.02656  -0.0115   0.0170   1.0000
  14.500   1.5102   0.03449   0.02811  -0.0098   0.0167   1.0000
  14.750   1.5149   0.03614   0.02985  -0.0081   0.0164   1.0000
  15.000   1.5175   0.03801   0.03182  -0.0064   0.0162   1.0000
  15.250   1.5177   0.04019   0.03409  -0.0049   0.0160   1.0000
  15.500   1.5198   0.04229   0.03631  -0.0038   0.0159   1.0000
  15.750   1.5203   0.04462   0.03877  -0.0028   0.0157   1.0000
  16.000   1.5191   0.04724   0.04152  -0.0020   0.0156   1.0000
  16.250   1.5165   0.05018   0.04459  -0.0016   0.0154   1.0000
  16.500   1.5118   0.05349   0.04804  -0.0015   0.0153   1.0000
  16.750   1.5054   0.05727   0.05195  -0.0018   0.0152   1.0000
  17.000   1.4971   0.06153   0.05636  -0.0027   0.0151   1.0000
  17.250   1.4863   0.06645   0.06143  -0.0042   0.0149   1.0000
  17.500   1.4722   0.07215   0.06729  -0.0064   0.0149   1.0000
  17.750   1.4547   0.07883   0.07414  -0.0094   0.0148   1.0000
  18.000   1.4330   0.08664   0.08213  -0.0133   0.0148   1.0000
  18.250   1.4066   0.09565   0.09133  -0.0180   0.0148   1.0000
  18.500   1.3771   0.10548   0.10134  -0.0232   0.0148   1.0000
  18.750   1.3462   0.11553   0.11157  -0.0285   0.0148   1.0000
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