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LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il)
Reynolds number: 50,000
Max Cl/Cd: 30.79 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c141c-il-50000-n5.txt
Download as CSV file: xf-c141c-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-141 BL426.57 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.5362   0.10051   0.09268  -0.0396   1.0000   0.0643
 -10.250  -0.5448   0.09494   0.08718  -0.0423   1.0000   0.0638
 -10.000  -0.5577   0.08852   0.08082  -0.0459   1.0000   0.0630
  -9.750  -0.5805   0.08145   0.07382  -0.0501   1.0000   0.0620
  -9.500  -0.6119   0.07609   0.06847  -0.0507   1.0000   0.0610
  -9.250  -0.6418   0.07184   0.06419  -0.0487   1.0000   0.0604
  -9.000  -0.6643   0.06779   0.06001  -0.0463   1.0000   0.0600
  -8.750  -0.6808   0.06402   0.05607  -0.0437   1.0000   0.0599
  -8.500  -0.6921   0.06047   0.05230  -0.0408   1.0000   0.0600
  -8.250  -0.6985   0.05714   0.04872  -0.0380   1.0000   0.0603
  -8.000  -0.7010   0.05398   0.04529  -0.0353   1.0000   0.0608
  -7.750  -0.6993   0.05118   0.04222  -0.0327   1.0000   0.0620
  -7.500  -0.6955   0.04850   0.03922  -0.0302   1.0000   0.0638
  -7.250  -0.6900   0.04569   0.03596  -0.0277   1.0000   0.0659
  -7.000  -0.6820   0.04281   0.03253  -0.0252   1.0000   0.0679
  -6.750  -0.6699   0.04015   0.02939  -0.0231   1.0000   0.0694
  -6.500  -0.6542   0.03837   0.02755  -0.0217   1.0000   0.0719
  -6.250  -0.6378   0.03682   0.02581  -0.0202   1.0000   0.0757
  -6.000  -0.6197   0.03499   0.02355  -0.0186   1.0000   0.0797
  -5.750  -0.5997   0.03322   0.02150  -0.0173   1.0000   0.0830
  -5.500  -0.5802   0.03203   0.02028  -0.0162   1.0000   0.0882
  -5.250  -0.5585   0.03076   0.01870  -0.0150   1.0000   0.0943
  -5.000  -0.5369   0.02955   0.01750  -0.0140   1.0000   0.0998
  -4.750  -0.5149   0.02862   0.01636  -0.0129   1.0000   0.1085
  -4.500  -0.4930   0.02765   0.01544  -0.0119   1.0000   0.1167
  -4.250  -0.4710   0.02682   0.01455  -0.0109   1.0000   0.1284
  -4.000  -0.4490   0.02603   0.01371  -0.0100   1.0000   0.1421
  -3.750  -0.4273   0.02524   0.01298  -0.0092   1.0000   0.1610
  -3.500  -0.4058   0.02443   0.01226  -0.0084   1.0000   0.1876
  -3.250  -0.3859   0.02352   0.01161  -0.0075   1.0000   0.2314
  -3.000  -0.3675   0.02225   0.01104  -0.0065   1.0000   0.3329
  -2.750  -0.3544   0.02091   0.01108  -0.0033   1.0000   0.5748
  -2.500  -0.3374   0.02073   0.01145   0.0008   1.0000   0.7499
  -2.250  -0.3054   0.02106   0.01186   0.0019   1.0000   0.8601
  -2.000  -0.2452   0.02171   0.01227  -0.0031   1.0000   0.9443
  -1.750  -0.1397   0.02237   0.01246  -0.0181   1.0000   1.0000
  -1.500  -0.1365   0.02218   0.01215  -0.0148   1.0000   1.0000
  -1.250  -0.1313   0.02206   0.01189  -0.0117   1.0000   1.0000
  -1.000  -0.1241   0.02200   0.01170  -0.0090   1.0000   1.0000
  -0.750  -0.1150   0.02200   0.01158  -0.0065   1.0000   1.0000
  -0.500  -0.0840   0.02225   0.01165  -0.0082   0.9945   1.0000
  -0.250  -0.0509   0.02251   0.01178  -0.0102   0.9874   1.0000
   0.000  -0.0178   0.02282   0.01196  -0.0122   0.9806   1.0000
   0.250   0.0152   0.02313   0.01218  -0.0141   0.9733   1.0000
   0.500   0.0466   0.02343   0.01241  -0.0156   0.9657   1.0000
   0.750   0.0807   0.02379   0.01270  -0.0176   0.9584   1.0000
   1.000   0.1103   0.02408   0.01297  -0.0187   0.9498   1.0000
   1.250   0.1461   0.02446   0.01332  -0.0209   0.9427   1.0000
   1.500   0.1737   0.02474   0.01361  -0.0215   0.9328   1.0000
   1.750   0.2086   0.02508   0.01397  -0.0235   0.9249   1.0000
   2.000   0.2390   0.02537   0.01431  -0.0245   0.9151   1.0000
   2.250   0.2685   0.02566   0.01465  -0.0253   0.9046   1.0000
   2.500   0.3054   0.02592   0.01499  -0.0273   0.8953   1.0000
   2.750   0.3393   0.02609   0.01528  -0.0287   0.8835   1.0000
   3.000   0.3705   0.02621   0.01551  -0.0294   0.8697   1.0000
   3.250   0.4044   0.02622   0.01565  -0.0303   0.8551   1.0000
   3.500   0.4460   0.02588   0.01550  -0.0321   0.8377   1.0000
   3.750   0.4811   0.02534   0.01513  -0.0322   0.8148   1.0000
   4.000   0.5240   0.02443   0.01445  -0.0331   0.7912   1.0000
   4.250   0.5516   0.02384   0.01403  -0.0316   0.7636   1.0000
   4.500   0.5813   0.02315   0.01351  -0.0301   0.7316   1.0000
   4.750   0.6073   0.02263   0.01311  -0.0282   0.6899   1.0000
   5.000   0.6374   0.02206   0.01259  -0.0266   0.6289   1.0000
   5.250   0.6710   0.02179   0.01190  -0.0253   0.5127   1.0000
   5.500   0.6848   0.02274   0.01200  -0.0220   0.3793   1.0000
   5.750   0.6916   0.02414   0.01277  -0.0185   0.2915   1.0000
   6.000   0.7016   0.02551   0.01369  -0.0158   0.2360   1.0000
   6.250   0.7153   0.02678   0.01470  -0.0138   0.1986   1.0000
   6.500   0.7310   0.02802   0.01575  -0.0121   0.1722   1.0000
   6.750   0.7501   0.02920   0.01688  -0.0108   0.1512   1.0000
   7.000   0.7710   0.03038   0.01805  -0.0098   0.1344   1.0000
   7.250   0.7952   0.03161   0.01930  -0.0093   0.1208   1.0000
   7.500   0.8206   0.03292   0.02065  -0.0089   0.1095   1.0000
   7.750   0.8459   0.03434   0.02201  -0.0087   0.1007   1.0000
   8.000   0.8718   0.03582   0.02374  -0.0084   0.0922   1.0000
   8.250   0.8975   0.03755   0.02547  -0.0082   0.0864   1.0000
   8.500   0.9197   0.03930   0.02754  -0.0074   0.0802   1.0000
   8.750   0.9413   0.04111   0.02942  -0.0068   0.0762   1.0000
   9.000   0.9604   0.04346   0.03211  -0.0057   0.0725   1.0000
   9.250   0.9750   0.04570   0.03472  -0.0041   0.0687   1.0000
   9.500   0.9888   0.04784   0.03707  -0.0026   0.0659   1.0000
   9.750   1.0025   0.05027   0.03964  -0.0013   0.0641   1.0000
  10.000   1.0093   0.05324   0.04296   0.0009   0.0626   1.0000
  10.250   1.0064   0.05649   0.04673   0.0040   0.0611   1.0000
  10.500   0.9996   0.05976   0.05042   0.0072   0.0598   1.0000
  10.750   0.9888   0.06299   0.05398   0.0104   0.0588   1.0000
  11.000   0.9738   0.06629   0.05755   0.0136   0.0581   1.0000
  11.250   0.9553   0.06999   0.06150   0.0162   0.0577   1.0000
  11.500   0.9327   0.07433   0.06608   0.0177   0.0576   1.0000
  11.750   0.9055   0.07963   0.07159   0.0178   0.0578   1.0000
  12.000   0.8740   0.08636   0.07848   0.0158   0.0583   1.0000
  12.250   0.8403   0.09498   0.08722   0.0112   0.0592   1.0000
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