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LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: LOCKHEED C-141 BL426.57 AIRFOIL (c141c-il)
Reynolds number: 200,000
Max Cl/Cd: 66.89 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-c141c-il-200000.txt
Download as CSV file: xf-c141c-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5373   0.10149   0.09765  -0.0432   1.0000   0.0686
 -10.500  -0.5661   0.09272   0.08893  -0.0525   1.0000   0.0689
 -10.250  -0.5940   0.08766   0.08385  -0.0554   1.0000   0.0690
 -10.000  -0.5638   0.08467   0.08097  -0.0498   1.0000   0.0706
  -9.750  -0.5579   0.08285   0.07916  -0.0475   1.0000   0.0715
  -9.500  -0.5745   0.07810   0.07445  -0.0496   1.0000   0.0721
  -9.250  -0.6037   0.07439   0.07076  -0.0486   1.0000   0.0723
  -9.000  -0.6326   0.07186   0.06823  -0.0446   1.0000   0.0724
  -8.750  -0.6500   0.06919   0.06554  -0.0414   1.0000   0.0731
  -8.500  -0.6655   0.06648   0.06279  -0.0383   1.0000   0.0739
  -8.250  -0.7615   0.04796   0.04292  -0.0292   1.0000   0.0471
  -8.000  -0.7623   0.04400   0.03879  -0.0264   1.0000   0.0460
  -7.750  -0.7622   0.04012   0.03459  -0.0232   1.0000   0.0450
  -7.500  -0.7589   0.03628   0.03033  -0.0201   1.0000   0.0444
  -7.250  -0.7504   0.03311   0.02672  -0.0175   1.0000   0.0445
  -7.000  -0.7374   0.03085   0.02405  -0.0153   1.0000   0.0457
  -6.750  -0.7217   0.02896   0.02175  -0.0133   1.0000   0.0468
  -6.500  -0.7038   0.02748   0.01986  -0.0115   1.0000   0.0476
  -6.250  -0.6834   0.02477   0.01694  -0.0107   1.0000   0.0491
  -6.000  -0.6623   0.02367   0.01578  -0.0098   1.0000   0.0509
  -5.750  -0.6411   0.02293   0.01494  -0.0088   1.0000   0.0536
  -5.500  -0.6194   0.02225   0.01406  -0.0077   1.0000   0.0566
  -5.250  -0.5968   0.02090   0.01259  -0.0070   1.0000   0.0594
  -5.000  -0.5750   0.02020   0.01192  -0.0061   1.0000   0.0628
  -4.750  -0.5459   0.01977   0.01138  -0.0067   0.9986   0.0679
  -4.500  -0.5123   0.01881   0.01045  -0.0082   0.9962   0.0735
  -4.250  -0.4764   0.01850   0.01007  -0.0101   0.9936   0.0810
  -4.000  -0.4448   0.01775   0.00942  -0.0113   0.9904   0.0893
  -3.750  -0.4109   0.01724   0.00894  -0.0129   0.9872   0.1008
  -3.500  -0.3749   0.01680   0.00857  -0.0150   0.9845   0.1168
  -3.250  -0.3429   0.01633   0.00823  -0.0162   0.9809   0.1420
  -3.000  -0.3116   0.01567   0.00790  -0.0175   0.9768   0.1967
  -2.750  -0.2810   0.01432   0.00766  -0.0193   0.9741   0.4176
  -2.500  -0.2512   0.01343   0.00789  -0.0197   0.9718   0.6726
  -2.250  -0.2257   0.01331   0.00807  -0.0187   0.9669   0.7668
  -2.000  -0.1981   0.01335   0.00827  -0.0180   0.9620   0.8276
  -1.750  -0.1656   0.01356   0.00854  -0.0181   0.9585   0.8759
  -1.500  -0.1343   0.01383   0.00880  -0.0182   0.9544   0.9118
  -1.250  -0.1012   0.01408   0.00901  -0.0188   0.9493   0.9410
  -1.000  -0.0509   0.01440   0.00926  -0.0231   0.9474   0.9602
  -0.750   0.0083   0.01472   0.00950  -0.0294   0.9469   0.9739
  -0.500   0.0899   0.01510   0.00982  -0.0403   0.9503   0.9887
  -0.250   0.1548   0.01516   0.00985  -0.0482   0.9504   0.9971
   0.000   0.2018   0.01509   0.00975  -0.0527   0.9469   1.0000
   0.250   0.2444   0.01496   0.00961  -0.0562   0.9434   1.0000
   0.500   0.2694   0.01487   0.00952  -0.0563   0.9346   1.0000
   0.750   0.3116   0.01471   0.00936  -0.0595   0.9302   1.0000
   1.000   0.3675   0.01436   0.00904  -0.0652   0.9276   1.0000
   1.250   0.4045   0.01388   0.00859  -0.0667   0.9165   1.0000
   1.500   0.4507   0.01305   0.00779  -0.0694   0.9048   1.0000
   1.750   0.4884   0.01237   0.00713  -0.0705   0.8946   1.0000
   2.000   0.5166   0.01190   0.00669  -0.0700   0.8831   1.0000
   2.250   0.5393   0.01157   0.00639  -0.0685   0.8692   1.0000
   2.500   0.5625   0.01124   0.00609  -0.0670   0.8543   1.0000
   2.750   0.5859   0.01092   0.00579  -0.0656   0.8377   1.0000
   3.000   0.6079   0.01067   0.00556  -0.0639   0.8175   1.0000
   3.250   0.6303   0.01046   0.00534  -0.0622   0.7927   1.0000
   3.500   0.6530   0.01029   0.00514  -0.0606   0.7613   1.0000
   3.750   0.6749   0.01025   0.00499  -0.0588   0.7189   1.0000
   4.000   0.6950   0.01039   0.00490  -0.0567   0.6569   1.0000
   4.250   0.7091   0.01085   0.00492  -0.0536   0.5647   1.0000
   4.500   0.7139   0.01177   0.00517  -0.0489   0.4371   1.0000
   4.750   0.7160   0.01292   0.00563  -0.0442   0.3137   1.0000
   5.000   0.7227   0.01395   0.00614  -0.0405   0.2259   1.0000
   5.250   0.7334   0.01481   0.00668  -0.0375   0.1758   1.0000
   5.500   0.7462   0.01557   0.00722  -0.0348   0.1454   1.0000
   5.750   0.7608   0.01624   0.00778  -0.0323   0.1245   1.0000
   6.000   0.7758   0.01692   0.00838  -0.0300   0.1095   1.0000
   6.250   0.7913   0.01765   0.00904  -0.0278   0.0979   1.0000
   6.500   0.8070   0.01846   0.00976  -0.0257   0.0883   1.0000
   6.750   0.8261   0.01904   0.01039  -0.0240   0.0805   1.0000
   7.000   0.8433   0.02003   0.01131  -0.0223   0.0739   1.0000
   7.250   0.8634   0.02067   0.01202  -0.0209   0.0683   1.0000
   7.500   0.8830   0.02194   0.01320  -0.0198   0.0630   1.0000
   7.750   0.9042   0.02263   0.01402  -0.0185   0.0591   1.0000
   8.000   0.9256   0.02354   0.01495  -0.0175   0.0557   1.0000
   8.250   0.9506   0.02543   0.01680  -0.0175   0.0525   1.0000
   8.500   0.9716   0.02629   0.01787  -0.0162   0.0500   1.0000
   8.750   0.9926   0.02732   0.01902  -0.0152   0.0475   1.0000
   9.000   1.0141   0.02856   0.02032  -0.0143   0.0456   1.0000
   9.250   1.0379   0.03077   0.02256  -0.0142   0.0440   1.0000
   9.500   1.0566   0.03324   0.02535  -0.0130   0.0430   1.0000
   9.750   1.0711   0.03504   0.02749  -0.0109   0.0422   1.0000
  10.000   1.0831   0.03707   0.02987  -0.0086   0.0411   1.0000
  10.250   1.0927   0.03924   0.03235  -0.0062   0.0401   1.0000
  10.500   1.0991   0.04180   0.03524  -0.0035   0.0394   1.0000
  10.750   1.0998   0.04493   0.03873  -0.0003   0.0392   1.0000
  11.000   1.0931   0.04850   0.04268   0.0036   0.0393   1.0000
  11.250   1.0775   0.05227   0.04683   0.0082   0.0396   1.0000
  11.500   1.0564   0.05617   0.05103   0.0128   0.0401   1.0000
  11.750   1.0328   0.06027   0.05541   0.0165   0.0406   1.0000
  12.000   1.0081   0.06467   0.06004   0.0190   0.0411   1.0000
  12.250   0.9828   0.06948   0.06505   0.0202   0.0416   1.0000
  12.500   0.9571   0.07489   0.07062   0.0199   0.0420   1.0000
  12.750   0.9318   0.08101   0.07688   0.0182   0.0425   1.0000
  13.000   0.9130   0.08745   0.08339   0.0160   0.0431   1.0000
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