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LOCKHEED C-5A BL1256 AIRFOIL (c5e-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: LOCKHEED C-5A BL1256 AIRFOIL (c5e-il)
Reynolds number: 50,000
Max Cl/Cd: 31.34 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-c5e-il-50000-n5.txt
Download as CSV file: xf-c5e-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: LOCKHEED C-5A BL1256 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.5086   0.12197   0.11401  -0.0081   1.0000   0.1309
 -10.000  -0.5069   0.11821   0.11028  -0.0099   1.0000   0.1315
  -9.500  -0.5390   0.10065   0.09270  -0.0261   1.0000   0.0784
  -9.250  -0.5289   0.09722   0.08930  -0.0255   1.0000   0.0774
  -9.000  -0.5276   0.09282   0.08493  -0.0274   1.0000   0.0765
  -8.750  -0.5321   0.08788   0.08003  -0.0306   1.0000   0.0759
  -8.500  -0.5409   0.08324   0.07541  -0.0332   1.0000   0.0755
  -8.250  -0.5486   0.07878   0.07093  -0.0352   1.0000   0.0753
  -8.000  -0.5543   0.07442   0.06651  -0.0366   1.0000   0.0753
  -7.750  -0.5577   0.07023   0.06222  -0.0375   1.0000   0.0753
  -7.500  -0.5586   0.06620   0.05804  -0.0378   1.0000   0.0751
  -7.250  -0.5569   0.06231   0.05398  -0.0377   1.0000   0.0747
  -7.000  -0.5530   0.05859   0.05007  -0.0373   1.0000   0.0744
  -6.750  -0.5472   0.05507   0.04631  -0.0366   1.0000   0.0743
  -6.500  -0.5394   0.05174   0.04272  -0.0356   1.0000   0.0744
  -6.250  -0.5299   0.04868   0.03934  -0.0345   1.0000   0.0753
  -6.000  -0.5191   0.04573   0.03598  -0.0333   1.0000   0.0769
  -5.750  -0.5065   0.04292   0.03267  -0.0320   1.0000   0.0783
  -5.500  -0.4917   0.04063   0.03019  -0.0307   1.0000   0.0793
  -5.250  -0.4756   0.03868   0.02810  -0.0295   1.0000   0.0802
  -5.000  -0.4589   0.03691   0.02614  -0.0283   1.0000   0.0813
  -4.750  -0.4416   0.03532   0.02437  -0.0271   1.0000   0.0828
  -4.500  -0.4236   0.03395   0.02281  -0.0259   1.0000   0.0856
  -4.250  -0.4046   0.03254   0.02111  -0.0247   1.0000   0.0889
  -4.000  -0.3842   0.03114   0.01932  -0.0235   1.0000   0.0913
  -3.750  -0.3644   0.02993   0.01812  -0.0226   1.0000   0.0933
  -3.500  -0.3444   0.02902   0.01718  -0.0216   1.0000   0.0963
  -3.250  -0.3238   0.02826   0.01633  -0.0206   1.0000   0.1011
  -3.000  -0.2993   0.02744   0.01534  -0.0200   0.9989   0.1062
  -2.750  -0.2629   0.02658   0.01455  -0.0218   0.9927   0.1118
  -2.500  -0.2266   0.02593   0.01378  -0.0234   0.9856   0.1213
  -2.250  -0.1919   0.02526   0.01317  -0.0250   0.9786   0.1317
  -2.000  -0.1560   0.02459   0.01254  -0.0268   0.9716   0.1452
  -1.750  -0.1232   0.02397   0.01197  -0.0283   0.9630   0.1644
  -1.500  -0.0872   0.02327   0.01138  -0.0306   0.9560   0.1930
  -1.250  -0.0550   0.02235   0.01075  -0.0324   0.9472   0.2434
  -1.000  -0.0368   0.02047   0.01113  -0.0298   0.9410   0.7020
  -0.750  -0.0181   0.02072   0.01153  -0.0259   0.9311   0.8077
  -0.500   0.0090   0.02094   0.01175  -0.0240   0.9232   0.8690
  -0.250   0.0457   0.02109   0.01183  -0.0244   0.9158   0.9168
   0.000   0.1096   0.02122   0.01185  -0.0305   0.9124   0.9582
   0.250   0.2102   0.02123   0.01173  -0.0444   0.9128   1.0000
   0.500   0.2364   0.02126   0.01170  -0.0449   0.9006   1.0000
   0.750   0.2651   0.02129   0.01169  -0.0457   0.8898   1.0000
   1.000   0.2941   0.02132   0.01169  -0.0464   0.8793   1.0000
   1.250   0.3150   0.02145   0.01180  -0.0457   0.8666   1.0000
   1.500   0.3383   0.02158   0.01193  -0.0453   0.8552   1.0000
   1.750   0.3669   0.02166   0.01201  -0.0456   0.8455   1.0000
   2.000   0.3858   0.02191   0.01226  -0.0445   0.8328   1.0000
   2.250   0.4094   0.02215   0.01252  -0.0439   0.8217   1.0000
   2.500   0.4396   0.02226   0.01267  -0.0443   0.8122   1.0000
   2.750   0.4628   0.02245   0.01290  -0.0434   0.7981   1.0000
   3.000   0.4900   0.02243   0.01293  -0.0426   0.7820   1.0000
   3.250   0.5209   0.02205   0.01257  -0.0415   0.7617   1.0000
   3.500   0.5428   0.02179   0.01233  -0.0391   0.7341   1.0000
   3.750   0.5660   0.02140   0.01195  -0.0366   0.7033   1.0000
   4.000   0.5879   0.02108   0.01162  -0.0341   0.6695   1.0000
   4.250   0.6100   0.02096   0.01153  -0.0321   0.6370   1.0000
   4.500   0.6319   0.02081   0.01137  -0.0299   0.5949   1.0000
   4.750   0.6510   0.02077   0.01116  -0.0271   0.5252   1.0000
   5.000   0.6654   0.02131   0.01088  -0.0237   0.3779   1.0000
   5.250   0.6732   0.02309   0.01157  -0.0209   0.2461   1.0000
   5.500   0.6869   0.02466   0.01268  -0.0194   0.1967   1.0000
   5.750   0.7030   0.02603   0.01380  -0.0181   0.1721   1.0000
   6.000   0.7211   0.02725   0.01493  -0.0169   0.1556   1.0000
   6.250   0.7404   0.02844   0.01603  -0.0158   0.1430   1.0000
   6.500   0.7611   0.02959   0.01710  -0.0149   0.1326   1.0000
   6.750   0.7851   0.03070   0.01829  -0.0142   0.1242   1.0000
   7.000   0.8106   0.03193   0.01943  -0.0138   0.1184   1.0000
   7.250   0.8383   0.03314   0.02078  -0.0136   0.1125   1.0000
   7.500   0.8642   0.03439   0.02206  -0.0133   0.1069   1.0000
   7.750   0.8911   0.03583   0.02356  -0.0132   0.1026   1.0000
   8.000   0.9180   0.03748   0.02541  -0.0130   0.0992   1.0000
   8.250   0.9426   0.03911   0.02715  -0.0127   0.0958   1.0000
   8.500   0.9667   0.04080   0.02878  -0.0125   0.0927   1.0000
   8.750   0.9862   0.04290   0.03135  -0.0116   0.0895   1.0000
   9.000   1.0052   0.04522   0.03399  -0.0108   0.0873   1.0000
   9.250   1.0228   0.04743   0.03644  -0.0100   0.0849   1.0000
   9.500   1.0401   0.04947   0.03860  -0.0094   0.0824   1.0000
   9.750   1.0539   0.05204   0.04136  -0.0084   0.0804   1.0000
  10.000   1.0578   0.05531   0.04515  -0.0066   0.0790   1.0000
  10.250   1.0582   0.05873   0.04902  -0.0049   0.0777   1.0000
  10.500   1.0546   0.06219   0.05287  -0.0031   0.0764   1.0000
  10.750   1.0474   0.06569   0.05668  -0.0014   0.0752   1.0000
  11.000   1.0351   0.06921   0.06045   0.0004   0.0743   1.0000
  11.250   1.0172   0.07314   0.06462   0.0017   0.0738   1.0000
  11.500   0.9922   0.07812   0.06983   0.0016   0.0737   1.0000
  11.750   0.9564   0.08513   0.07708  -0.0009   0.0742   1.0000
  12.000   0.9109   0.09537   0.08750  -0.0070   0.0753   1.0000
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