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E64 (8.45%) (e64-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E64 (8.45%) (e64-il)
Reynolds number: 50,000
Max Cl/Cd: 41.48 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e64-il-50000.txt
Download as CSV file: xf-e64-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E64  (8.45%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.4002   0.10075   0.09427  -0.0226   1.0000   0.2290
  -7.250  -0.3826   0.09605   0.08957  -0.0210   1.0000   0.2380
  -7.000  -0.4136   0.09664   0.09039  -0.0193   1.0000   0.2438
  -6.750  -0.3950   0.09201   0.08573  -0.0173   1.0000   0.2545
  -6.500  -0.4074   0.09022   0.08409  -0.0156   1.0000   0.2616
  -6.250  -0.4218   0.08910   0.08311  -0.0153   1.0000   0.2731
  -6.000  -0.4102   0.08537   0.07941  -0.0120   1.0000   0.2847
  -5.750  -0.4101   0.08273   0.07685  -0.0100   1.0000   0.2958
  -5.500  -0.4129   0.08039   0.07460  -0.0081   1.0000   0.3122
  -5.250  -0.4175   0.07826   0.07256  -0.0066   1.0000   0.3295
  -5.000  -0.4218   0.07595   0.07034  -0.0053   1.0000   0.3483
  -4.750  -0.4152   0.07308   0.06753  -0.0014   1.0000   0.3671
  -4.250  -0.3169   0.04645   0.03898  -0.0567   1.0000   0.1279
  -4.000  -0.2926   0.04237   0.03473  -0.0580   1.0000   0.1223
  -3.750  -0.2544   0.03732   0.02872  -0.0621   1.0000   0.1122
  -3.500  -0.2233   0.03395   0.02483  -0.0635   1.0000   0.1095
  -3.250  -0.1912   0.03112   0.02142  -0.0646   1.0000   0.1095
  -3.000  -0.1600   0.02906   0.01865  -0.0650   1.0000   0.1141
  -2.750  -0.1330   0.02731   0.01679  -0.0649   1.0000   0.1266
  -2.500  -0.1061   0.02569   0.01499  -0.0643   1.0000   0.1432
  -2.250  -0.0798   0.02413   0.01371  -0.0640   1.0000   0.1962
  -2.000  -0.0481   0.02160   0.01257  -0.0642   1.0000   0.4377
  -1.750  -0.0397   0.02020   0.01253  -0.0582   1.0000   0.6999
  -1.500  -0.0395   0.01903   0.01176  -0.0515   1.0000   1.0000
  -1.250  -0.0076   0.01930   0.01124  -0.0537   1.0000   1.0000
  -1.000   0.0184   0.01962   0.01107  -0.0544   1.0000   1.0000
  -0.750   0.0428   0.01999   0.01104  -0.0547   1.0000   1.0000
  -0.500   0.0663   0.02040   0.01110  -0.0549   1.0000   1.0000
  -0.250   0.0890   0.02084   0.01126  -0.0550   1.0000   1.0000
   0.000   0.1111   0.02133   0.01152  -0.0551   1.0000   1.0000
   0.250   0.1327   0.02187   0.01184  -0.0551   1.0000   1.0000
   0.500   0.1538   0.02245   0.01223  -0.0551   1.0000   1.0000
   0.750   0.1745   0.02308   0.01270  -0.0551   1.0000   1.0000
   1.000   0.1946   0.02376   0.01326  -0.0551   1.0000   1.0000
   1.250   0.2142   0.02449   0.01389  -0.0551   1.0000   1.0000
   1.500   0.2334   0.02528   0.01458  -0.0551   1.0000   1.0000
   1.750   0.2521   0.02614   0.01537  -0.0552   1.0000   1.0000
   2.000   0.2703   0.02705   0.01623  -0.0553   1.0000   1.0000
   2.250   0.3033   0.02834   0.01749  -0.0582   0.9922   1.0000
   2.500   0.3546   0.02989   0.01903  -0.0643   0.9743   1.0000
   2.750   0.4014   0.03117   0.02033  -0.0693   0.9558   1.0000
   3.000   0.4457   0.03227   0.02148  -0.0736   0.9366   1.0000
   3.250   0.4962   0.03333   0.02264  -0.0786   0.9182   1.0000
   3.500   0.5328   0.03412   0.02353  -0.0810   0.8970   1.0000
   3.750   0.5812   0.03479   0.02434  -0.0850   0.8770   1.0000
   4.000   0.6192   0.03535   0.02509  -0.0870   0.8549   1.0000
   4.250   0.6703   0.03552   0.02548  -0.0904   0.8340   1.0000
   4.500   0.7076   0.03574   0.02590  -0.0916   0.8103   1.0000
   4.750   0.7632   0.03511   0.02562  -0.0944   0.7883   1.0000
   5.000   0.8131   0.03419   0.02502  -0.0958   0.7638   1.0000
   5.250   0.8664   0.03272   0.02392  -0.0968   0.7377   1.0000
   5.500   0.9228   0.03062   0.02225  -0.0972   0.7091   1.0000
   5.750   0.9818   0.02803   0.02001  -0.0971   0.6744   1.0000
   6.000   1.0199   0.02668   0.01887  -0.0950   0.6293   1.0000
   6.250   1.0527   0.02581   0.01800  -0.0923   0.5750   1.0000
   6.500   1.0738   0.02589   0.01794  -0.0888   0.5133   1.0000
   6.750   1.0912   0.02648   0.01821  -0.0851   0.4463   1.0000
   7.000   1.1032   0.02766   0.01906  -0.0813   0.3785   1.0000
   7.250   1.1144   0.02930   0.02023  -0.0779   0.3134   1.0000
   7.500   1.1236   0.03136   0.02190  -0.0744   0.2510   1.0000
   7.750   1.1277   0.03341   0.02354  -0.0708   0.1955   1.0000
   8.000   1.1361   0.03596   0.02564  -0.0679   0.1487   1.0000
   8.250   1.1582   0.03924   0.02872  -0.0667   0.1185   1.0000
   8.500   1.1872   0.04295   0.03265  -0.0663   0.1047   1.0000
   8.750   1.2096   0.04617   0.03611  -0.0652   0.0958   1.0000
   9.000   1.2250   0.04990   0.04032  -0.0635   0.0907   1.0000
   9.250   1.2361   0.05381   0.04479  -0.0613   0.0880   1.0000
   9.500   1.2426   0.05807   0.04957  -0.0589   0.0871   1.0000
   9.750   1.2427   0.06252   0.05453  -0.0562   0.0870   1.0000
  10.000   1.2366   0.06713   0.05961  -0.0534   0.0876   1.0000
  10.250   1.2251   0.07176   0.06464  -0.0507   0.0884   1.0000
  10.500   1.2083   0.07629   0.06949  -0.0480   0.0893   1.0000
  10.750   1.1875   0.08064   0.07407  -0.0455   0.0903   1.0000
  11.000   1.1657   0.08535   0.07897  -0.0440   0.0912   1.0000
  11.250   1.1453   0.09056   0.08432  -0.0438   0.0921   1.0000
  11.500   1.1299   0.09630   0.09016  -0.0445   0.0931   1.0000
  11.750   1.1011   0.10289   0.09691  -0.0471   0.0947   1.0000
  12.000   1.0164   0.12117   0.11516  -0.0633   0.1029   1.0000
  12.250   1.0099   0.12908   0.12304  -0.0669   0.1054   1.0000
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