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LOCKHEED C-141 BL0 AIRFOIL (c141a-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-141 BL0 AIRFOIL (c141a-il)
Reynolds number: 100,000
Max Cl/Cd: 42.04 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c141a-il-100000-n5.txt
Download as CSV file: xf-c141a-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.7264   0.07271   0.06664  -0.0685   1.0000   0.0397
 -12.500  -0.7850   0.06351   0.05713  -0.0717   1.0000   0.0391
 -12.250  -0.8170   0.05904   0.05247  -0.0706   1.0000   0.0391
 -12.000  -0.8425   0.05590   0.04916  -0.0677   1.0000   0.0392
 -11.750  -0.8655   0.05352   0.04662  -0.0635   1.0000   0.0394
 -11.500  -0.8880   0.05166   0.04462  -0.0581   1.0000   0.0396
 -11.250  -0.9077   0.05000   0.04282  -0.0524   1.0000   0.0398
 -11.000  -0.9205   0.04811   0.04075  -0.0475   1.0000   0.0403
 -10.750  -0.9299   0.04623   0.03866  -0.0430   1.0000   0.0409
 -10.500  -0.9368   0.04428   0.03646  -0.0386   1.0000   0.0418
 -10.250  -0.9422   0.04217   0.03398  -0.0344   1.0000   0.0429
 -10.000  -0.9427   0.04019   0.03167  -0.0306   1.0000   0.0440
  -9.750  -0.9343   0.03912   0.03056  -0.0281   1.0000   0.0450
  -9.500  -0.9258   0.03795   0.02929  -0.0255   1.0000   0.0462
  -9.250  -0.9168   0.03656   0.02771  -0.0229   1.0000   0.0476
  -9.000  -0.9066   0.03510   0.02598  -0.0204   1.0000   0.0493
  -8.750  -0.8948   0.03369   0.02429  -0.0180   1.0000   0.0513
  -8.500  -0.8809   0.03279   0.02340  -0.0162   1.0000   0.0529
  -8.250  -0.8663   0.03184   0.02235  -0.0143   1.0000   0.0549
  -8.000  -0.8507   0.03079   0.02109  -0.0124   1.0000   0.0574
  -7.750  -0.8343   0.02977   0.01992  -0.0108   1.0000   0.0599
  -7.500  -0.8178   0.02899   0.01915  -0.0092   1.0000   0.0623
  -7.250  -0.7976   0.02817   0.01822  -0.0082   0.9994   0.0654
  -7.000  -0.7703   0.02727   0.01717  -0.0086   0.9971   0.0692
  -6.750  -0.7428   0.02654   0.01645  -0.0092   0.9948   0.0731
  -6.500  -0.7154   0.02585   0.01563  -0.0095   0.9925   0.0778
  -6.250  -0.6895   0.02511   0.01492  -0.0097   0.9898   0.0824
  -6.000  -0.6622   0.02452   0.01426  -0.0101   0.9871   0.0882
  -5.750  -0.6342   0.02391   0.01365  -0.0107   0.9847   0.0945
  -5.500  -0.6066   0.02341   0.01310  -0.0111   0.9821   0.1022
  -5.250  -0.5819   0.02284   0.01258  -0.0109   0.9787   0.1106
  -5.000  -0.5548   0.02234   0.01210  -0.0112   0.9756   0.1212
  -4.750  -0.5258   0.02189   0.01168  -0.0120   0.9729   0.1352
  -4.500  -0.4972   0.02144   0.01130  -0.0126   0.9702   0.1531
  -4.250  -0.4737   0.02097   0.01093  -0.0122   0.9661   0.1762
  -4.000  -0.4468   0.02048   0.01061  -0.0125   0.9625   0.2111
  -3.750  -0.4186   0.01988   0.01033  -0.0132   0.9595   0.2688
  -3.500  -0.3914   0.01912   0.01011  -0.0138   0.9568   0.3689
  -3.250  -0.3734   0.01844   0.01003  -0.0120   0.9518   0.4889
  -3.000  -0.3484   0.01814   0.01017  -0.0112   0.9478   0.5925
  -2.750  -0.3187   0.01811   0.01035  -0.0112   0.9445   0.6621
  -2.500  -0.2895   0.01818   0.01048  -0.0112   0.9412   0.7088
  -2.250  -0.2672   0.01820   0.01053  -0.0098   0.9354   0.7424
  -2.000  -0.2379   0.01829   0.01063  -0.0097   0.9313   0.7730
  -1.750  -0.2043   0.01844   0.01081  -0.0104   0.9283   0.8002
  -1.500  -0.1781   0.01859   0.01097  -0.0096   0.9234   0.8256
  -1.250  -0.1504   0.01881   0.01122  -0.0089   0.9182   0.8542
  -1.000  -0.1139   0.01915   0.01157  -0.0098   0.9150   0.8807
  -0.750  -0.0728   0.01939   0.01178  -0.0121   0.9125   0.8974
  -0.500  -0.0417   0.01951   0.01186  -0.0128   0.9072   0.9098
  -0.250  -0.0043   0.01965   0.01197  -0.0149   0.9023   0.9187
   0.000   0.0357   0.01973   0.01202  -0.0174   0.8986   0.9276
   0.250   0.0812   0.01980   0.01208  -0.0211   0.8961   0.9343
   0.500   0.1125   0.01990   0.01218  -0.0221   0.8890   0.9440
   0.750   0.1543   0.01995   0.01223  -0.0252   0.8844   0.9507
   1.000   0.1984   0.01992   0.01222  -0.0286   0.8810   0.9571
   1.250   0.2411   0.01994   0.01228  -0.0319   0.8756   0.9622
   1.500   0.2787   0.01991   0.01230  -0.0341   0.8687   0.9697
   1.750   0.3280   0.01972   0.01217  -0.0384   0.8649   0.9729
   2.000   0.3688   0.01942   0.01194  -0.0409   0.8539   0.9782
   2.250   0.4138   0.01866   0.01123  -0.0433   0.8386   0.9821
   2.500   0.4568   0.01795   0.01058  -0.0455   0.8199   0.9858
   2.750   0.4971   0.01746   0.01017  -0.0475   0.8013   0.9910
   3.000   0.5357   0.01707   0.00986  -0.0493   0.7783   0.9962
   3.250   0.5754   0.01661   0.00944  -0.0512   0.7492   1.0000
   3.500   0.6060   0.01617   0.00895  -0.0510   0.7115   1.0000
   3.750   0.6435   0.01581   0.00839  -0.0520   0.6524   1.0000
   4.000   0.6684   0.01590   0.00812  -0.0508   0.5706   1.0000
   4.250   0.6809   0.01640   0.00810  -0.0477   0.4731   1.0000
   4.500   0.6861   0.01717   0.00832  -0.0435   0.3782   1.0000
   4.750   0.6911   0.01796   0.00866  -0.0394   0.3040   1.0000
   5.000   0.6984   0.01867   0.00904  -0.0358   0.2512   1.0000
   5.250   0.7079   0.01930   0.00944  -0.0326   0.2134   1.0000
   5.500   0.7180   0.01990   0.00987  -0.0296   0.1855   1.0000
   5.750   0.7296   0.02045   0.01031  -0.0267   0.1641   1.0000
   6.000   0.7414   0.02102   0.01079  -0.0239   0.1473   1.0000
   6.250   0.7535   0.02159   0.01129  -0.0211   0.1341   1.0000
   6.500   0.7654   0.02221   0.01183  -0.0183   0.1231   1.0000
   6.750   0.7787   0.02278   0.01240  -0.0158   0.1133   1.0000
   7.000   0.7918   0.02342   0.01301  -0.0133   0.1053   1.0000
   7.250   0.8051   0.02408   0.01363  -0.0109   0.0983   1.0000
   7.500   0.8193   0.02477   0.01435  -0.0086   0.0921   1.0000
   7.750   0.8333   0.02546   0.01503  -0.0064   0.0866   1.0000
   8.000   0.8482   0.02626   0.01584  -0.0043   0.0818   1.0000
   8.250   0.8642   0.02702   0.01665  -0.0025   0.0771   1.0000
   8.500   0.8788   0.02791   0.01748  -0.0006   0.0734   1.0000
   8.750   0.8973   0.02879   0.01849   0.0008   0.0694   1.0000
   9.000   0.9140   0.02967   0.01941   0.0023   0.0660   1.0000
   9.250   0.9301   0.03069   0.02036   0.0038   0.0632   1.0000
   9.500   0.9490   0.03175   0.02164   0.0050   0.0600   1.0000
   9.750   0.9658   0.03280   0.02278   0.0064   0.0573   1.0000
  10.000   0.9811   0.03384   0.02379   0.0079   0.0552   1.0000
  10.250   0.9981   0.03517   0.02529   0.0092   0.0528   1.0000
  10.500   1.0139   0.03655   0.02688   0.0106   0.0507   1.0000
  10.750   1.0275   0.03782   0.02825   0.0122   0.0490   1.0000
  11.000   1.0404   0.03902   0.02946   0.0138   0.0475   1.0000
  11.250   1.0517   0.04067   0.03130   0.0155   0.0460   1.0000
  11.750   1.0658   0.04438   0.03555   0.0198   0.0432   1.0000
  12.000   1.0711   0.04625   0.03761   0.0219   0.0423   1.0000
  12.250   1.0756   0.04806   0.03955   0.0239   0.0415   1.0000
  12.500   1.0800   0.04983   0.04141   0.0257   0.0408   1.0000
  12.750   1.0808   0.05204   0.04376   0.0276   0.0401   1.0000
  13.000   1.0678   0.05528   0.04740   0.0303   0.0395   1.0000
  13.250   1.0524   0.05884   0.05129   0.0324   0.0389   1.0000
  13.500   1.0347   0.06279   0.05555   0.0338   0.0385   1.0000
  13.750   1.0139   0.06732   0.06038   0.0343   0.0381   1.0000
  14.000   0.9890   0.07277   0.06610   0.0338   0.0380   1.0000
  14.250   0.9579   0.07972   0.07333   0.0315   0.0380   1.0000
  14.500   0.9169   0.08944   0.08333   0.0264   0.0384   1.0000
  14.750   0.8581   0.10533   0.09948   0.0161   0.0392   1.0000
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