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LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il)
Reynolds number: 50,000
Max Cl/Cd: 31.22 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141c-il-50000.txt
Download as CSV file: xf-c141c-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4654   0.10977   0.10216  -0.0158   1.0000   0.3162
  -9.250  -0.4622   0.10676   0.09918  -0.0149   1.0000   0.3317
  -9.000  -0.4593   0.10377   0.09623  -0.0139   1.0000   0.3473
  -8.750  -0.4568   0.10080   0.09331  -0.0128   1.0000   0.3627
  -8.500  -0.4540   0.09783   0.09038  -0.0116   1.0000   0.3784
  -8.250  -0.4480   0.09486   0.08744  -0.0100   1.0000   0.3964
  -8.000  -0.4552   0.09296   0.08563  -0.0077   1.0000   0.4189
  -7.750  -0.4451   0.08963   0.08233  -0.0058   1.0000   0.4395
  -7.500  -0.4368   0.08653   0.07925  -0.0041   1.0000   0.4575
  -7.250  -0.4385   0.08382   0.07659  -0.0021   1.0000   0.4721
  -7.000  -0.6565   0.06133   0.05367  -0.0265   1.0000   0.1677
  -6.750  -0.6662   0.05597   0.04760  -0.0246   1.0000   0.1547
  -6.500  -0.6561   0.05219   0.04362  -0.0229   1.0000   0.1529
  -6.250  -0.6460   0.04851   0.03968  -0.0212   1.0000   0.1506
  -6.000  -0.6351   0.04506   0.03582  -0.0194   1.0000   0.1493
  -5.750  -0.6222   0.04211   0.03236  -0.0176   1.0000   0.1512
  -5.500  -0.6068   0.03942   0.02905  -0.0158   1.0000   0.1535
  -5.250  -0.5876   0.03670   0.02598  -0.0146   1.0000   0.1561
  -5.000  -0.5671   0.03473   0.02392  -0.0135   1.0000   0.1634
  -4.750  -0.5453   0.03278   0.02144  -0.0122   1.0000   0.1705
  -4.500  -0.5219   0.03096   0.01959  -0.0114   1.0000   0.1798
  -4.250  -0.4982   0.02938   0.01788  -0.0105   1.0000   0.1929
  -4.000  -0.4729   0.02791   0.01632  -0.0098   1.0000   0.2086
  -3.750  -0.4469   0.02664   0.01495  -0.0090   1.0000   0.2320
  -3.500  -0.4201   0.02524   0.01382  -0.0085   1.0000   0.2660
  -3.250  -0.3948   0.02361   0.01268  -0.0079   1.0000   0.3289
  -3.000  -0.1396   0.02415   0.01486  -0.0355   1.0000   1.0000
  -2.750  -0.1408   0.02368   0.01426  -0.0322   1.0000   1.0000
  -2.500  -0.1415   0.02327   0.01373  -0.0287   1.0000   1.0000
  -2.250  -0.1417   0.02292   0.01326  -0.0252   1.0000   1.0000
  -2.000  -0.1412   0.02262   0.01283  -0.0216   1.0000   1.0000
  -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   0.01190  -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  -0.1041   0.02206   0.01150  -0.0043   1.0000   1.0000
  -0.250  -0.0914   0.02219   0.01151  -0.0025   1.0000   1.0000
   0.000  -0.0772   0.02237   0.01158  -0.0009   1.0000   1.0000
   0.250  -0.0619   0.02259   0.01171   0.0005   1.0000   1.0000
   0.500  -0.0457   0.02287   0.01189   0.0017   1.0000   1.0000
   0.750  -0.0289   0.02319   0.01214   0.0027   1.0000   1.0000
   1.000  -0.0116   0.02355   0.01244   0.0036   1.0000   1.0000
   1.250   0.0060   0.02396   0.01280   0.0044   1.0000   1.0000
   1.500   0.0238   0.02442   0.01322   0.0051   1.0000   1.0000
   1.750   0.0417   0.02492   0.01370   0.0057   1.0000   1.0000
   2.000   0.0597   0.02546   0.01424   0.0062   1.0000   1.0000
   2.250   0.0776   0.02606   0.01484   0.0067   1.0000   1.0000
   2.500   0.0954   0.02670   0.01550   0.0070   1.0000   1.0000
   2.750   0.1131   0.02740   0.01623   0.0073   1.0000   1.0000
   3.000   0.1306   0.02816   0.01703   0.0076   1.0000   1.0000
   3.250   0.1477   0.02899   0.01791   0.0077   1.0000   1.0000
   3.500   0.1646   0.02988   0.01887   0.0078   1.0000   1.0000
   3.750   0.2018   0.03131   0.02043   0.0039   0.9909   1.0000
   4.000   0.2729   0.03326   0.02262  -0.0060   0.9611   1.0000
   4.250   0.3495   0.03461   0.02428  -0.0156   0.9261   1.0000
   4.500   0.4102   0.03492   0.02489  -0.0212   0.8884   1.0000
   4.750   0.4875   0.03423   0.02463  -0.0276   0.8487   1.0000
   5.000   0.5721   0.03172   0.02266  -0.0326   0.8052   1.0000
   5.250   0.6413   0.02793   0.01946  -0.0329   0.7530   1.0000
   5.500   0.7087   0.02270   0.01449  -0.0290   0.6192   1.0000
   5.750   0.7241   0.02416   0.01381  -0.0226   0.3735   1.0000
   6.000   0.7438   0.02649   0.01534  -0.0208   0.2918   1.0000
   6.250   0.7755   0.02856   0.01704  -0.0211   0.2435   1.0000
   6.750   0.8375   0.03269   0.02090  -0.0216   0.1913   1.0000
   7.000   0.8644   0.03488   0.02318  -0.0211   0.1763   1.0000
   7.250   0.8866   0.03713   0.02569  -0.0199   0.1648   1.0000
   7.500   0.9094   0.03979   0.02852  -0.0190   0.1566   1.0000
   7.750   0.9261   0.04214   0.03125  -0.0171   0.1488   1.0000
   8.000   0.9472   0.04535   0.03449  -0.0162   0.1437   1.0000
   8.250   0.9545   0.04829   0.03807  -0.0131   0.1411   1.0000
   8.500   0.9599   0.05142   0.04170  -0.0101   0.1381   1.0000
   8.750   0.9641   0.05478   0.04546  -0.0073   0.1360   1.0000
   9.000   0.9628   0.05875   0.04986  -0.0042   0.1365   1.0000
   9.250   0.9561   0.06305   0.05456  -0.0012   0.1381   1.0000
   9.500   0.9474   0.06748   0.05929   0.0016   0.1399   1.0000
   9.750   0.9383   0.07201   0.06405   0.0038   0.1415   1.0000
  10.000   0.9317   0.07672   0.06892   0.0055   0.1430   1.0000
  10.250   0.9334   0.08182   0.07413   0.0064   0.1443   1.0000
  10.500   0.8482   0.08901   0.08157   0.0081   0.1574   1.0000
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