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12% JOUKOWSKI AIRFOIL (joukowsk-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: 12% JOUKOWSKI AIRFOIL (joukowsk-il)
Reynolds number: 50,000
Max Cl/Cd: 26.44 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-joukowsk-il-50000-n5.txt
Download as CSV file: xf-joukowsk-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 12% JOUKOWSKI 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.7858   0.09575   0.08806   0.0060   1.0000   0.0877
 -11.500  -0.8944   0.07122   0.06329  -0.0127   1.0000   0.0838
 -11.250  -0.9288   0.06370   0.05553  -0.0173   1.0000   0.0837
 -11.000  -0.9435   0.05944   0.05110  -0.0185   1.0000   0.0850
 -10.750  -0.9555   0.05582   0.04728  -0.0185   1.0000   0.0865
 -10.500  -0.9622   0.05222   0.04337  -0.0183   1.0000   0.0888
 -10.250  -0.9656   0.04857   0.03926  -0.0179   1.0000   0.0914
 -10.000  -0.9528   0.04649   0.03714  -0.0173   1.0000   0.0947
  -9.750  -0.9400   0.04458   0.03513  -0.0167   1.0000   0.0989
  -9.500  -0.9302   0.04196   0.03209  -0.0161   1.0000   0.1037
  -9.250  -0.9129   0.04032   0.03048  -0.0155   1.0000   0.1086
  -9.000  -0.8968   0.03853   0.02850  -0.0149   1.0000   0.1147
  -8.750  -0.8790   0.03679   0.02663  -0.0143   1.0000   0.1210
  -8.500  -0.8605   0.03531   0.02503  -0.0137   1.0000   0.1288
  -8.250  -0.8409   0.03388   0.02356  -0.0131   1.0000   0.1366
  -8.000  -0.8212   0.03244   0.02192  -0.0125   1.0000   0.1467
  -7.750  -0.8006   0.03129   0.02081  -0.0119   1.0000   0.1566
  -7.500  -0.7798   0.03014   0.01965  -0.0113   1.0000   0.1681
  -7.250  -0.7584   0.02902   0.01850  -0.0107   1.0000   0.1810
  -7.000  -0.7369   0.02801   0.01745  -0.0101   1.0000   0.1956
  -6.750  -0.7149   0.02706   0.01651  -0.0095   1.0000   0.2112
  -6.500  -0.6927   0.02620   0.01567  -0.0089   1.0000   0.2284
  -6.250  -0.6702   0.02540   0.01490  -0.0083   1.0000   0.2468
  -6.000  -0.6473   0.02465   0.01414  -0.0078   1.0000   0.2667
  -5.750  -0.6242   0.02397   0.01347  -0.0072   1.0000   0.2876
  -5.500  -0.6010   0.02337   0.01296  -0.0065   1.0000   0.3081
  -5.250  -0.5776   0.02281   0.01242  -0.0058   1.0000   0.3302
  -5.000  -0.5540   0.02228   0.01191  -0.0052   1.0000   0.3530
  -4.750  -0.5304   0.02182   0.01155  -0.0044   1.0000   0.3746
  -4.500  -0.5068   0.02139   0.01114  -0.0037   1.0000   0.3975
  -4.250  -0.4832   0.02099   0.01079  -0.0029   1.0000   0.4201
  -4.000  -0.4599   0.02064   0.01053  -0.0020   1.0000   0.4418
  -3.750  -0.4369   0.02030   0.01024  -0.0011   1.0000   0.4643
  -3.500  -0.4143   0.01999   0.00999  -0.0002   1.0000   0.4866
  -3.250  -0.3925   0.01972   0.00982   0.0010   1.0000   0.5074
  -3.000  -0.3723   0.01948   0.00966   0.0023   1.0000   0.5287
  -2.750  -0.3532   0.01926   0.00950   0.0037   1.0000   0.5501
  -2.500  -0.3352   0.01909   0.00941   0.0052   1.0000   0.5709
  -2.250  -0.3187   0.01898   0.00938   0.0070   1.0000   0.5909
  -2.000  -0.2749   0.01897   0.00943   0.0039   0.9771   0.6173
  -1.750  -0.2299   0.01899   0.00951   0.0008   0.9569   0.6427
  -1.500  -0.1887   0.01899   0.00956  -0.0013   0.9352   0.6674
  -1.250  -0.1495   0.01899   0.00960  -0.0029   0.9134   0.6915
  -1.000  -0.1132   0.01900   0.00966  -0.0036   0.8917   0.7137
  -0.750  -0.0823   0.01901   0.00969  -0.0034   0.8682   0.7361
  -0.500  -0.0530   0.01901   0.00969  -0.0027   0.8458   0.7586
  -0.250  -0.0258   0.01902   0.00972  -0.0014   0.8238   0.7795
   0.000   0.0000   0.01902   0.00973   0.0000   0.8011   0.8011
   0.250   0.0257   0.01902   0.00972   0.0014   0.7795   0.8238
   0.500   0.0530   0.01901   0.00969   0.0027   0.7586   0.8458
   0.750   0.0822   0.01900   0.00969   0.0034   0.7360   0.8682
   1.000   0.1132   0.01900   0.00966   0.0036   0.7137   0.8917
   1.250   0.1494   0.01899   0.00960   0.0029   0.6915   0.9134
   1.500   0.1887   0.01899   0.00956   0.0013   0.6674   0.9352
   1.750   0.2299   0.01899   0.00951  -0.0008   0.6428   0.9570
   2.000   0.2749   0.01897   0.00943  -0.0039   0.6172   0.9772
   2.250   0.3186   0.01897   0.00938  -0.0070   0.5909   1.0000
   2.500   0.3352   0.01909   0.00941  -0.0052   0.5710   1.0000
   2.750   0.3531   0.01926   0.00950  -0.0037   0.5501   1.0000
   3.000   0.3723   0.01948   0.00966  -0.0023   0.5287   1.0000
   3.250   0.3925   0.01972   0.00982  -0.0010   0.5075   1.0000
   3.500   0.4143   0.01999   0.00998   0.0002   0.4866   1.0000
   3.750   0.4369   0.02030   0.01023   0.0011   0.4643   1.0000
   4.000   0.4599   0.02064   0.01053   0.0020   0.4418   1.0000
   4.250   0.4832   0.02099   0.01079   0.0029   0.4201   1.0000
   4.500   0.5068   0.02139   0.01114   0.0037   0.3975   1.0000
   4.750   0.5304   0.02182   0.01155   0.0044   0.3746   1.0000
   5.000   0.5539   0.02228   0.01191   0.0052   0.3530   1.0000
   5.250   0.5776   0.02281   0.01242   0.0058   0.3302   1.0000
   5.500   0.6010   0.02337   0.01296   0.0065   0.3082   1.0000
   5.750   0.6242   0.02397   0.01347   0.0072   0.2876   1.0000
   6.000   0.6473   0.02465   0.01414   0.0078   0.2667   1.0000
   6.250   0.6701   0.02540   0.01489   0.0084   0.2468   1.0000
   6.500   0.6927   0.02620   0.01567   0.0090   0.2284   1.0000
   6.750   0.7149   0.02706   0.01651   0.0096   0.2112   1.0000
   7.000   0.7368   0.02801   0.01745   0.0101   0.1956   1.0000
   7.250   0.7584   0.02902   0.01850   0.0107   0.1810   1.0000
   7.500   0.7797   0.03014   0.01965   0.0113   0.1682   1.0000
   7.750   0.8006   0.03129   0.02081   0.0119   0.1566   1.0000
   8.000   0.8212   0.03244   0.02192   0.0125   0.1467   1.0000
   8.250   0.8409   0.03388   0.02356   0.0131   0.1366   1.0000
   8.500   0.8604   0.03531   0.02503   0.0137   0.1287   1.0000
   8.750   0.8789   0.03679   0.02663   0.0143   0.1210   1.0000
   9.000   0.8967   0.03852   0.02849   0.0149   0.1148   1.0000
   9.250   0.9128   0.04031   0.03047   0.0155   0.1085   1.0000
   9.500   0.9303   0.04195   0.03209   0.0161   0.1038   1.0000
   9.750   0.9400   0.04457   0.03512   0.0167   0.0990   1.0000
  10.000   0.9529   0.04648   0.03713   0.0173   0.0947   1.0000
  10.250   0.9655   0.04856   0.03927   0.0179   0.0914   1.0000
  10.500   0.9622   0.05221   0.04336   0.0183   0.0888   1.0000
  10.750   0.9556   0.05581   0.04727   0.0185   0.0866   1.0000
  11.000   0.9436   0.05942   0.05108   0.0186   0.0850   1.0000
  11.250   0.9288   0.06369   0.05552   0.0173   0.0837   1.0000
  11.500   0.8940   0.07126   0.06333   0.0127   0.0838   1.0000
  11.750   0.7856   0.09577   0.08807  -0.0060   0.0876   1.0000
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